NASA-TM-88442 (q19:l · 2013-08-30 · nasa technical memorandum nasa tm-88442 tests with three-dimensional adjustments in the rectangular working section of the french t2 wind tunnel,

NASA-TM-88442

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NASA TECHNICAL MEMORANDUM NASA TM-88442

TESTS WITH THREE-DIMENSIONAL ADJUSTMENTS IN THE RECTANGULAR WORKING SECTION OF THE FRENCH T2 WIND TUNNEL, WITH AN

AS 07-TYPE SWEPT-BACK WING MODEL

A. Blanchard, M. J. Payry, J. F. Breil

Translation of "Essais 'd'adaptation tridirnensionnelle' de la veine rectangulaire de la soufflerie T2, en presence d'une rnaquette d'aile en fleche du type AS 07," Rapport Technique OA 34/3075 (DERAT 12/5015 ON), O.N.E.R.A., Centre d'Etudes et de Recherches de Toulouse, November 1985, pp. 1-24 (plus figures).

,LANGLE.Y RESEARCH CENTER LIBRARY, NASA

HAMPTON, VIRGINIA

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, DC 20!546 JULY 1986

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Administration 1,(. 5pon,o"n, Apency Co~.

cry NOlet Translation of "Essais 'd'adaptation tridimensionnelle' de la veine rec1: fleche du O.N.E.R.A. 1-24 (plus

angulaire de la soufflerie T2, en presence d'une maquette type AS 07, " Rapport Technique OA 34/3075 (D~HAT 12/5015 , Centre d'Etudes et de Recherches de Toulouse, November figures).

d'aile en DN) , 1985, pp.

1~. Ab.troc' This report presents the results obtained on 'the AS 07 wing and the working se "non-adapt which comp

ction walls for three types of configurations .. The first, called ed, .. corresponds to the divergent upper and lower rectilinear walls ensate for limit layer thickening. It can serve as a basis for com·· calculations. The second configuration corresponds to wall shapes from calculation's which tend to minimize interference at the level of

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. plete flow determined the fuse;I.-a tion," use determine not suffie dinated :wi

Finally., the third configuratiotl, called "two-dimensional: adap.ta-s the st~ndard method, for T2 profile tests. This case was tested to the influence of wall shape and error magnitude. These results are ient to validate' the three-dimensional adaptation; they must be coo;r-th caiculations or wi,th ' un 1 imi ted atmosphere tests.

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TABLE OF CONTENTS

NOTATION

1 - INTRODUCTION

2 - ADAPTATION PRINCIPLE

2.1 Two-dimensional adaptation

2.2 Three-dimensional adaptation

3 - EXPERIMENT EQUIPMENT

3.1 Working section equipment

3.2 Mounting the wing

3.3 Acquisition and examination program

4 .- SUMMARY OF TESTS MADE

5 - CON'I'ROL TESTS

5.1 Angling by wall rotation

5.2 Iteration convergences

5.2.1 Three-dimensional adaptation

5.2.2 Two-dimensional adaptation

5.3 Non /2.0/3.0 comparison

5.4 Visualizations

6 - SYSTEMATIC TESTS

7 - CONCLUSION

REFERENCES

LIST OF FIGURES

ANNEX 1 - Cz

2 - Kp

3 - File listing

4

5

7

8

8

9

9

10

11

13

17

17

17

17

18

18

20

21

22

24

25

3

NOTATION

::] Cartesian coordinates in the reference working section

Zp (porthole axis)

Y

X

Z

)

Cartesian coordinates in the wing reference (leading

edge to socket)

C Profile chord of the wing section considered

Angle of the model (fuselage axis)

Mo Infinite Mach upstream of the flow

M Local Mach (wing or wall)

Pressure coefficient

Cz Local or complete-wing lift coefficient

f C, locoL

l CL =

4

'rESTS WITH THREE-DIMENSIONAL ADJUSTMENTS IN THE RECTANGULAR WORKING SECTION OF THE FRENCH T2 WIND TUNNEL, WITH AN

AS 07-TYPE SWEPT-BACK WING MODEL


1 ... INTRODUCTION

This test series follows a study done in the T2 wind tunnel

with the goal of defining a shape for the adaptable walls which

would minimize their influence on three-dimensional objects

placed in the center of the section or fastened on the side.

The present configuration of the working section does not

allow obtaining a shape identical to that of the layer of

current existing around a three-dimensional model in unlimited

atmosphere (two completely rectilinear and parallel lateral

walls, two flexible and bendable upper and lower walls). The

planned solution thus consists of using the two bendable walls

to minimize the influence of the walls on the model.

The method implemented uses solutions developed by "E.

Wedemeyer and L. Lamarche" [5]. A first series of tests was

done in cooperation with the University of Berlin on various

existing models [6]:

- a C5 revolving body 166 mm long, 0.3% blockage;

- a civil F4 airplane model with 120-mm wingspan and three-

component balance;

- a duck-type military airplane model with the same balance.

Another series of tests was then done on a bigger model [7]:

- a C5 body 400 mm long, 1.8% blockage.

*Numbers; in the margin indicate pagination in the foreign text.

5

The results and calculations were compared.

The calculation method was optimized for revolving bodies

placed in the center of the section; an extrapolation was tried

which placed a half-wing at the wall. In this case, calculation

is done as if the section were twice its actual width, using the

Mach distribution at the wall measured near the plane of

symmetry.

The results obtained on the "16/1000-scale" AS 07 are

discussed in this report. They can be divided into two groups:

control tests and systematic tests.

Included in the first group is control of wing angling by

rotating the walls. The path of the jacks would not permit the

displacements required by calculation for angling the model to

+2·; we thus used this artifidial method after having verified

its validity.

The three-dimensional adaptation method supplies the

optimal shape of the walls from the first calculation, whatever

the initial position of the walls; this was verified in 18 several test configurations. Finally, an adaptation called

"two-dimensional" was tested; it uses the normal method for T2

profile tests. This case, without theoretical justification,

was tried to see the influence of the shape of the walls and the

size of errors which can be made.

The second part of this study corresponds to systematic

tE~StS: four configurations were chosen which gave different

lift coefficients, without making highly supersonic zones appear

on the profiles. For each configuration, three wall positions

were tested:

- The first, called "unadapted," corresponds to the upper

and lower divergent rectilinear walls compensating for

6

thickening of the limit layers; it served as our basis

for beginning three-dimensional adaptation calculations.

These particularly simple limit conditions can also be

used for complete calculation of the flow in the working

section.

- The second wall shape comes from the three-dimensional

adaptation calculation; the flexible sheets are

positioned before the gust.

- Finally, the last case corresponds to "two-dimensional'

adaptation"; the iterative process converges on a single

gust.

For each type of test, three gusts are necessary to obtain

readings from the six rows of pressure recorders spread along

the AS 07 wing.

The experimental results gathered during this series are not: sufficient to validate the three-dimensional adaptation

method used. Additional calculations must be made to estimate

residual corrections. In these tests, a negligible influence of

the walls is observed for low lift values or low Mach numbers;

inversely, for 2 degrees of incidence or for Mach 0.8, the gaps

become significant and can in part be interpreted as variations

in aerodynamic incidence.

2 - ADAPTATION PRINCIPLE

The purpose of the adaptable walls is to create an

unlimited flow around a model in a working section with finite

dimensions; this can be done by controlling the wall conditions,

either by their shape in the case of solid walls or by flows of

mass through porous walls. The first solution has been chosen

at T2, where flexible sheets moved by jacks form the upper and

lower plates of the working section [3].

7

In the case of a three-dimensional body, it is necessary to

bend the walls located around the model to arrive at a shape

near the layer of current existing around the model in unlimited

atmosphere. This solution is not at present possible at T2, but

on the other hand it is possible to use the two flexible /9

walls to minimize residual corrections due to the influence of

the walls on the object.


The details of the process will be found in [2] and

[4]; it uses a coupling between the real flow in the working

section (internal field) and a calculated virtual flow outside

the wind tunnel (external field). Coupling occurs on a control

surface near the walls through speed vector components.

Adaptation is achieved by an iterative process acting on the

shape of the walls: the components of the speed on the control

surface become available at each iteration; they are

extrapolated from the pressure measurements at the wall. The

velocities needed on the control surface to achieve an unlimited

external flow are calculated by the Green function following an

inverse method. A method of optimized relaxation between the

internal and external flows for the vertical velocity component,

followed by an integration along each flexible wall, supplies

the new shape of the wall. The real shape needed is obtained by

adding the thickness displacement of the four wall limit layers.

2.2 Three-dimensional adaptation

For three-dimensional adaptation, the process is

different [5]: it uses schematization of the model through

distribution of sources and vortices in a narrow horseshoe

placed on the section axis. This schematization gives a good

representation of axis ymmetrica 1 bodies mounted in the middle of

the working section.

8

The originality of the method lies in then doing a

linear transformation, which permits passing directly from

distribution of velocities at the walls to the adapted form

without needing to determine the intensity of singularities.

The optimized shape of the walls is thus theoretically obtained

from the first calculation; this shape, which is not exactly

"adapted," minimizes residual corrections on the model caused by

the influence of the walls.

Using this method for a half-wing at the wall is

abusive, because the base schematization does not represent a

wingspanJ it has nonetheless been tried here by replacing the

lateral door by a plane of symmetry leading to a fictional

double section width, and taking the Mach distribution of the

flexible walls near the plane of symmetry as reference.

3 '- EXPERIMENTAL EQUIPMEN'I'

The T2 transonic wind tunnel is pressurizable and can

function at low temperaturesJ only minimum-pressure and ambient

temperature tests were done during this series.

3.1 Working section equipment

The working section has an almost square section of

0.39 x 0.37 mm 2 at the entrance. Flexible sheets of Invar

make up the upper and lower walls, equipped with three rows of

pr.essur4~ recorders whose coordinates are given in figures 7 and

8. The sheet-positioning mechanism is described in [2], [3],

and [4].

The left lateral door has three portholes with

pressure recorders placed along horizontal and vertical lines

whose coordinates are shown in figures 7 and 9.

9

The pressure recorders are linked to the Scanivalves,

each of whose head can observe 48 positions in 5 seconds.

The position of the wing in the working section is

given in figure 6.

The Mach number of the flow is set by a second neck

controlled by the computer which controls the gust.

No other equipment or wind tunnel measurement method

was used.

3.2 Mounting the win~

The AS 07 wing model with a scale of "16/1000" is

shown by the photographs in figure 5. The method of mounting

the wing on the wall is shown (figure 6), the plane of the wing

and its specifications are given (figures 10 and 11), and the

shape of the profiles which compose it and the positions of the

pressure recorders are indicated (figures 12 and 13).

There are six rows, each with 16 recorders on the

inner and outer sections and one on the leading edge; they are

placed across the wingspan so as to form lines with constant

chord percentages. These recorders communicate with tubes

placed in grooves along the wingspan; each tube communicates

with three recorders (either on the external wing or on the

internal wing). When one of the three rows of recorders is used

to measure pressure, the other two are covered with thin (0.05-

mm) adhesive strips. It is thus possible to simultaneously

measure pressure on two sections of the wing (one internal and

one external); measurement of velocities over the entire wing

thus requires three different gusts.

The wing is mounted on a half-fuselage linked to a

porthole, whose rotation ensures the angling of the wing-

10

fuselage assembly; the angular reference is the rectilinear part

on the back of the fuselage [1].

3.3 Acquisition and examination program

The T2 wind tunnel is linked to a team of two

computers, one concerned with creating and regulating the gust

and the other with obtaining data and storing measurements to

disk at the end of the gust.

These tests are pursuant to the series done on the /11

C5 body and use its principal elements.

Disk car.~:ridge LU 26, Program

LU 34, Test files, calculation files

AC9uisit:Jon program

(TEACQ)

(RAFAL)L PARe 5

or

PARC S

(lance ACQC5)

(uses PROJ and ADAP.)

Fixed walls:

No adaptation

during gust

Two-dimensional

adaptation

Initialization of programs {With (TR,) RINC 5 (For PARC 5)

or (TR,) RINC S (For PARC S)

Test file

AD --- test number from AD 100 to AD 173

11

Wall posJ tioning file

- any test file AD---

- or calculation file AD 9 -._-

- or'special file AD 4: Divergent rectilinear walls of

symmetrical limit layers.

AD 444: AD 4 + 10' rotation upward

AD 445: AD 4 + 30' rotation upward

ThFee-dimensional adaptation calculation

Calculation from a test file AD

VKJ 43 Calculation of wall shapes without rotation

VKI M Calculation of wall shapes with rotation

LD

I ')J::=:=--I

~ - - - ---- - - - - - -. 780 "''''

---tFiling to disk

... J

I

:h:370 mm

, Of

- section length 780 mm

- ratio c = h/b = 2.1081

- reference recorders:

right lateral RL

weighting coefficients

file VKJ - R (cartridge

LU 43)

File for new calculated wall shapes

AD 9 --- beginning test number for the calculation

grograms for examination of AD--- files

l,TCS:

- graphs local profile Mach numbers

- graphs Kp

- lists AD file

- calculates Cz

12

LTC 51:

- graphs wall Mach numbers

- graphs wall shapes

starts LTC 52 (does an RP, LTC 52)

LTC VK:

- graphs only wall shapes calculated by VKI 43 or VKIM

(from AD 9---).

4 - SUMMARY OF TESTS PERFORMED

A previous study was done on the AS 07 wing [11. We

verified in one case that the same results would occur, although

the working section was modified when the T2 wind tunnel was

adapted for cryogenics.

The first control tests were done by measuring rows 2 and 5

of pressure recorders for the Mach numbers and incidences

indicated below:

Mo J 0,6 0,7 0,8 )

0( -) ( )

( +20 X X X )

( 0 x x x )

( _2 0 X X )

( )

13

Four configurations WE!re selected for systematic tests: /13

)

0,6 0,7 0,8)

--~~--~~--~--~~ x )

( ::) (--- ---:--:----)

(0° X: : X ) ( ::) (------- ------- -------:-------) (~2° X ) ( )

They correspond to a sampling of lift coefficients and to an

infinite Mach effect upstream, while limiting the supersonic

zones which appear on the profiles.

Figure 1 shows the list of tests in chronological order,

and figures 2, 3, and 4 classify them by configuration.

We first showed that rotation of the upper and lower walls

was equivalent to angling the model at the same angle. This

artifice was made necessary because the path of the jacks did

not permit the displacements required by calculation of

three-dimensional adaptation for a model incidence of +2-_

- Divergent rectilinear walls

·Mo ( )

I:l( ,( 0( _ ~~~I_ J 0, 6 0, 8 ) Ihf.naJ.. ( D\$ elAJ ,,"l1}..lU' )

( ) +20 ( +2° AD 4 AD 120 )

( +1,5° AD 445 AD 122 ) ( :) (----------- ----------_.-: -------------)

O· (0° AD 4 AD 107 - AD 109 AD 108 - AD 132 ) ( -0,5° AD 445 AD 137 AD 139 ) ( )

14

- Three-dimensional adapted walls

Mo

( )

( 0( CALCUL 0,6 0,8 )

0( aerod •• 0° ( ) (-- ) ( 0° VKI 43 117 AD 119 ) ( -0,5" VKI M 138 AD 141 ) ( )

The three-dimensional adaptation method theoretically

supplies the optimal shape of the walls from the first

calculation, whatever the initial position of the flexible

sheets. Controls were done in this respect for the following

configurations:

Mo ( ) ( .cl..

J. 0,7 0,8)

( .~p .. " ) ( ) ( +1,5° AD 127 (I) ) ( AD 128 (2) ) ( : AD 129 (3) )

(-------- ----------: ---------) ( :) ( 0° AD 115 (I) : AD 118 (I) ) ( AD 116 (2) : AD 119 (2) ) ( : .. ) (----- -------: --- ----)

( -0 , 5 ° AD 1 40 (I) ) ( AD 141 (2) ) ( : . )

The figure in parentheses after the file number indicates the

order of the iterationJ the wall-positioning file thus results

from calculation of the preceding test. (Iteration (0) is the

test done with rectilinear walls.)

/14

We also verified that the tests called "two-dimensional

adaptation" converged rapidly, as is the case for the profile

tests; it is sufficient for that to compare the wall position of

15

the 3rd and 4th iterations done during the same gust; the two

positions are always close. In general, the beginning shape

chosen is near the adapted shape, but we have tested this

convergence in the two particular cases when the beginning shape

was far from the adapted shape. The beginning file chosen was

AD 4: rectilinear walls divergent from limit layers and

symmetrical.

Configuration: Mo = 0.7 ~ = +1.5·

Configuration: Mo = 0.8 ~ = o· File AD 130 (1)

File AD 133 (1)

followed by File AD 134 (2)

Comparisons were made between the various wall positions;

they are noted:

- "Non," for divergent rectilinear walls

- "2D," for two-dimensional adaptation done with the PARCS

program - "3d," for positioning of the walls in the shape

calculated by the VKI 43 or VKI M program

It was decided to do systematic tests for the three cases

of "adaptation," the non-adapted case serving as a basis for

three-dimensional calculation (any wall shape will work); this

case can also serve as a basis for complete flow calculations,

because here the limit conditions are particularly simple. The

two-dimensional adaptation, a priori outside the subject of the

study, was systematically tested to use as a comparison with the

assumed optimal shape.

Finci11y, four configurations for three cases of adaptation,

reproduced three times to have the velocity field on all of the

wing, were tested; these 36 gusts make up the systematic tests

listed in figure 26a.

16

5 '. CONTROL TESTS

We will not present all the tests done, but only a

selection of cases judged most interesting, since the goal of

this series is not to evaluate the AS 07 wing.

5.1 Angling by wall rotation

Of the five configurations tested (paragraph 4), three

are presented. The first corresponds to Mo = 0.6 and ~ = +2·

for rectilinear walls (figure 14); this is the configuration

which obliged us to use this artifice, as the three-dimensional

case could not be tested.

Figure 15 shows the comparison of Mach numbers on the

walls and on the wing, for an aerodynamic incidence equal to o· and a Mach number equal to 0.8, in the case of rectilinear

walls. Figure 16 presents the same configurations but for wall

shapes coming respectively from calculations VKI 43 and VKI M.

The results of figures 14 and 15 show that the high

Mach case is the most recordable, but the correspondence of the

tests remains good. Figure 16 shows that the VKI M calculation

makes perfect allowance for total rotation.

It is thus possible to display a model incidence /16

different from that desired and to compensate by rotating the

walls.

5.2 Convergences of iterations


Several calculations for optimization of wall

shape were connected for one configuration. The last test is

always recalculated, leading to a wall shape which by definition

17

will not be used, but which will in fact constitute an

additional iteration.

Of the four tested cases, two are presented in

figures 17 and 18; the first (Mo = 0.7 and = 0·) shows that

the adapted shape is practically obtained from the first

iteration; in the second case--much more difficult (Mo = 0.8

and « = +2°)--it is necessary to wait for the second

calculation. This second case corresponds to a freely

supersonic regime of the wing which will not be studied

systematically herein.


In all tests done, the 3rd iteration is always

identical to the 4th and last iteration of the gust, even when

the upper and lower walls have been prepositioned in a shape

very different from the "adapted" shape. This is the case shown

in figure 19 corresponding to Mo = 0.8 and oc = 0·.

To confirm the validity of this statement, a

second test was done, positioning the flexible sheets on the

preceding shape; the values obtained can thus be considered to

correspond to the 4th, 5th p 6th, and 7th iterations of the test;

they are all identical (figure 20), which confirms that the

convergence was well obtained.

5.3 Non/2-D/3-D comparison

Two cases are presented here, one of which is not part

of the systematic tests:

- Mo = 0.7

- Mo = 0.8

18

The gaps observed following the types of "adaptation"

will become more significant as lift and Mach number upstream

increase. The adaptation called "two-dimensional" gives results

nearer to the non-adapted case; in fact, everything happens as

if the aerodynamic incidence of the two-dimensional case were

higher than that of the tests with a wall shape adapted in three

dimensions. On the other hand, rectilinear walls lead to a

higher effective Mach number upstream (blockage effect).

In the first case (figure 21), the gaps are moderate;

they are more significant in the second case (figure 22).

Observation of the direction of the walls leaving the convergent

(figure 21) shows that effectively the direction of the flow

upstream is no longer horizontal in the "2-D" case, unlike the

"3-D" case; the angular reference was given by the "non-adapted"

case. The effect produced is incontestable, because we /17

previously demonstrated that rotation of the wall assembly

modified the aerodynamic incidence of the model; however, this

is not sufficient to prove that the 2-D case is erroneous,

because the direction of the current lines in unlimited

atmosphere is not known. We note also the very different shapes

of the walls downstream; they go downward for the "3-D" cases,

which is logical allowing for the chosen schematization

(horseshoe vortex) and the calculation made (in the plane of

symmetry). But once more, that does not prove that the shape

obtained is optimum.

Finally, one can observe on the last figure (23) that

the effect produced by modifying the shape of the walls is not

constant across the wingspan. This was predictable due to the

working section geometry itself, allowing for twist of the wing

and for three-dimensional effects.

19

5.4 Visualizations

For three configurations, oil visualizations were done

on the left door of the working section, giving the direction of

the current lines 55.4 mm from the end of the wing. Reference

marks were made, making it possible to locate the positions

relative to the current lines and to measure their deviations.

W~Q..k"I\'lI -:.e(.~, .. 1')

Av.16

• &()o ... ~()o .200 - Zoo . -+. -. _ .. _.--. -·1--· -._.

I

The end of the wing is located between the abscissas

91.06 mm and 135.86 mm from the porthole (figure 6) and very

near to the section axis (function of the incidence).

The maximum deviations noticed are located on the

section axis slightly behind the tip of the wing (figures 24,

25, and 26).

( Walls dmax ) ( MQ 0( ) ( ) (

"Non-adapted"; )

Figure ( 0,6 +2° (S° •..•.. 6°) ) ( AD 4 ) ( -- - .:-------) ( ) ( 0,6 +2° · (S° ...... 6°) ) ( 'Adapted 2-D: ) Figure · . ( : --- -:-------) (---:--- · ) · ( 0,6 _2° "Non-adapted": "0,5- ) Figure ( ) ( AD 4 )

24

25

26

20

The photos taken from behind clearly show the /18

deviations of the current lines.


For the 36 gusts that made up the systematic tests

(paragraph 4 and figure 26a), the following information is

given: wall shape (figures 27 and 28), Mach numbers of the

three rows of recorders on the adaptable walls (figures 29, 30,

31 u and 32), Mach numbers of the left lateral door (figures 33,

346 35, and 36) following the horizontal axis or the three

verticals, and finally spread of Kp on the AS 07 wing (figures

37 to 44).

Numerical values for these curves are given in the attached

test listings. File numbers corresponding in chronological

order to the experiments were kept in the interests of clarity.

Here will be found a systematic comparison of the three

cases of adaptation--"Non/2-D/3-D"--and their influence on the

speed distributions whose principal characteristics were seen in

paragraph 5.3.

Finally, integration of Kp for each section supplies local

lift coefficient Cz. The values are tabulated in figure 45;

they were traced along the wingspan of the various

configurations tested (figures 46 and 47). It is observed that

the internal wing changes less rapidly than the external wing

with incidence (figure 46) or Mach number upstream (figure 47).

On the other hand, the gap between the "non-adapted" and

"adapted 3-D" cases increases with the lift.

21

Local Cz were multiplied by the chord of the profile in the

section considered; the product Cz • C represents local /19

contribution to wing lift. The values obtained were traced in

this representation (figures 48 and 49); this weighting mOdifies

the appearance of the curves ("elliptic" distribution plane),

but the observed tendencies are the same.

Finally, integration of the curves in this last

representation supplies the overall lift coefficient of the

wing, which was reported as a function of incidence (figure

50). We have also reported the lift measured during the

preceding series [1], done between rectilinear walls for a Mach

number upstream of 0.47. The effect of compressibility is felt

more as supersonic zones develop on the wing.

7 - CONCLUSION

This series of tests on the AS 07 wing is registered as a

study on three-dimensional adaptation of the T2 wind tunnel. It

uses the two flexible walls to minimize residual corrections in

the presence of a three-dimensional model. It implements the

"E. Wedemeyer and L. Lamarche" method where schematization of

the model by a distribution of singularities adequately

represents an axisymmetrical body. Extrapolation of these

methods in the case of a half-wing at the wall has no ultimate

goal; it serves merely as a preliminary phase, to observe the

influence of wall shape in various sections of the wing, to

study the convergence of the method, and to make adjustments

(rotation of walls, incidence, etc.,.

On the other hand, these experiments can serve as a basis

for calculating potential three-dimensional flow around the

model. Then, a three-dimensional object placed in the section

22

could be more elaborately schematicized; it would lead to

development, as for axisymmetrical bodies, of a method of

adaptation minimizing the influence of the walls on the model.

At present, it is difficult to know if the shape called

"adapted 3-D" is nearer to the values of unlimited atmosphere

than the shape "adapted 2-D," but it is definitely not the

optimum shape.

The tests will next be completed by directional limit layer

readings on the lateral wall at the level of the end of the

wing. The direction of the current lines in this area will be

an important element in the reality-calculation comparison.

23

REFERENCES

1. A. Mignosi, A. Seraudie. "Etude d'une maquette d'aile en fleche a la soufflerie T2 de l'ONERA-CERT [Study of a swept.-back wing model in the ONERA-CERT's T2 wind tunnel]." DE RAT technical note No. 13/5006 ON, March 1977.

2. J. P. Archambaud, J. P. Chevallier. "Utilisation de parois adaptables pour les essais en courant plan rUse of adaptable walls for tests in plane current]." ONERA TP No. 1982-3B, AGARD/FDP meeting in London, May 19-·20, 1982.

3. J. P. Archambaud, A. Seraudie. "Etudes de parois adaptables a T2 [Adaptable wall studies at T2]." ONERA TP NO. 1983-150, 20th AAAF Colloquium, Toulouse, November 8-10, 1983.

4. J. P. Chevallier, A. Mignosi, J. P. Archambaud, A. Seraudie. "Adaptable walls in the T2 wind tunnel: Principles, execution, and some examples of two-dimensional results." La Recherche A~rospatiale, 1983-4, pp. 217-235.

5. L. Lamarche, E. Wedemeyer. "Minimization of wall interference for three-dimensional models with two-dimensional wall adaptation." V.K.!. Technical note 149, Rhode Saint Genese, Belgium, March 1984.

6. J. P. Archambaud, J. B. Oor, A. Mignosi, L. Lamarche. Premiers essais d'adaptation des parois auto-adaptables bidE~msionnelles de la soufflerie T2 autour d'obstacles tridimensionnels [First. adaptation tests of two-dimensional self-adapting walls at the T2 wind tunnel around threedimensional obstacles]. OA Technical Report No. 33/3075 (DERAT 11/5015 DN), September 1985.

7. J. P. Archambaud, J. B. Dor, M. J. Payry. Rapport sur la deuxieme campagne du C5 [Report on the second C5 series]. (TO be published soon.)

24

LIST OF FIGURES

1. Test tables

- List of tests - Rows of recorders 1-4 - Rows of recorders 2-5 - Rows of recorders 3-6

2. Mounting the wing in the section

Figure

1 2 3 4

- Presentation of mounting 5 - Drawing of wing mounting 6 - Drawing of pressure recorders on walls 7 - Pressure recorder specifications - flexible walls 8 - Pressure recorder specifications - lateral portholes 9 - Plane of the wing 10 - Dimensions of the wing 11 - Profiles 12

Specifications of wing pressure recorders 13

3. Control tests

3.1 Rotation

- First control (~= +2·, Mo = 0.6 Non-adaptable) Wall shape Wall Mach Profile Mach

SE!cond control (r/.. = 0·, Mo = 0.8 Non-adaptable) Wall shape Wall Mach Profile Mach

Third control (0( = 0·, Mo = 0.8 3-D) Wall shape Wall Mach Profile Mach

3.2 Convergence of iterations

a .. 3-D

First case (0£= 0·, Mo = 0.7) Wall shape Profile Mach

Second case (ol= +2·, Mo = 0.8) Wall shape Profile Mach

14

15

16

17

18

25

b - 2 - D (0( = a ., Mo = o. 8 )

- Beginning of AD 4 (File AD 133) Wall shape Profile Mach

- Beginning of a similar shape: AD 133 (File AD 134) Wall shape

19

Profile Mach 20

3.3 Non/2-D/3-D comparison

- ( 0( = o· , Mo = 0.7) Wall shape Wall Mach 21

- (0<. = o· , Mo = 0.7) Profile Mach (2 ) Profile Mach (3 ) 21

- co(. = o· , Mo = 0.8) Wall shape Wall Mach 22

- (I>( = 0·, Mo = 0.8) Profile Mach (2) Profile Mach ( 3) 22

- (0(, = a·, Mo = 0.8) Kp 23

4. Visualization, left lateral door

- (O( = +2· , Mo = 0.6) Non - front Visu (2 ) - back 24

- (ex = +2·, Mo = 0.6) 2-D - front Visu ( 1) - back 25

- ( CI{ = +2· , Mo = 0.6) Non - front Visu (3) - back 26

5. Use in 4 base cases

5.1 Wall shaEe

-tol = -2· Mo = 0.6 _ot = +2· Mo = 0.6 27

-c:( = O· Mo = 0.6 -0( = O· Mo = 0.8 28

5.2 AdaEtable wall Mach

- (fI... = - 2 • Mo = O. 6 ) - Non - 2-D - 3-D 29

26

- (01. = o· Mo = 0.6) - Non - 2-D - 3-D 30

- (~ = +2· Mo = 0.6) - Non - 2-D - 3-D 31

- (~ = o· Mo = 0.8) - Non - 2-D - 3-D 32

5.3 Lateral wall Mach

- (Qt. = -2· Mo = 0.6) - Non - 2-D - 3-D 33

- (0£ = o • Mo = 0.6) - Non - 2-D - 3-D 34

- (0/. = +2· Mo = 0.6) - Non - 2-D - 3-D 35

- (oot = o· Mo = 0.8) - Non - 2-D - 3-D 36

5.4 !S£

- (cit = -2· Mo = 0.6) Non adaptable 37

- (cit = -2· Mo = 0.6) - Non - 2-D - 3-D 38

- «(:0( = O· Mo = 0.6) Non adaptable 39

- (c>( = o· Mo = 0.6) - Non - 2-D - 3-D 40

- ('coI. = +2· Mo = 0.6) Non adaptable 41

- (IOJI-= +2· Mo = 0.6) - Non - 2-D - 3-D 42

- (lOt. = o· Mo = 0.8) Non adaptable 43

27

- (0(.= o· Mo = 0.8) - Non - 2-D - 3-D

5.5 Cz

- Cz recapitulative - Cz Mo = 0.6 (3 inc.) - Cz Cot = O· (2 Mach) - Cz X chord Mo = 0.6 (3 inc.) - Cz X chord 0(. = O· (2 Mach) - Cz (oc.)

44

45 46 47 48 49 50

28

TEST TABLES

FIGURES 1 TO 4

29

Figure I

List of "AS 07 wing" tests

File AD4 Divergent ~li·ne·c1'r- walls AD445 · · Idem + 30' rotation (upward) AD--- · · Test file No. ---AD9---- · · 3-D calculation of new wall position

A File ?> c... v £

~ Rows of Recorders

*~*~~~***.**.~~~~*~~4*~~**~~**~~~~~~~~~*~ •• ~.*~**~*~*~~*.~~~~. "A 'HIC.' PFI~IGEES 'FICHtER ROT.' 'riB. i+ "F t ,:H I ER 'AFF. '~lACH DE PR t '~e::~ 'DE DEPART PARa I:3' ADAPT.' D' I TE? .. ~.~~****!**~*f~*~~ ~~~~*~*~~!~~~~.~.*; **;*~*!~~~*~~*!~~~~~~~~ ,.. AD 1 a~' a, .;' z. - ~ 'AD4 .a, NO~I , 1 ,;

c..Starting File

D Wall Rot.

E No. of iter.

" AD 1 07 .a .6 a 1 ;;. ;,; FtD10S 13 .:3 13 1 ,; ;;. AD11a -2 • (' a , .. , 1 It

,; AD11~ .a • (' AD'?la~.) '3-D 0)' 1 " ,; AD111i a ., AD'311~ 133-0 CZ" 1 ,; ,. ADlli' a .6 I1D':la7 a 3-D' 1 ,; ,; AD113 a .8 AD9108 a 3-D (1)' 1 ;,; ;or ADll'~ .) .:3 A0911S a :3-D (~;. 1 ,. "" AD lZ.a , +;2 , • .; AD4 a rlO~1 1;r * AD122 ,+1." • 6 ADH~ 313' NON 1 It

* AD123 '+1. 5' .6 I1D9122 30' '3-0 1" * AD124 '+1.5' •• A044~ 30' NO~I 1'" * AD12~ '+1.~ .7 AD9t;N 30'3-0 1;;. ,; AD 126 ,+ 1. 5 .3 AD44'5 :313' ~IOrl 1,; '" AD12? '+1. S .:3 AD9126 :313' ]-0 (1;' 1 ". ;or AD129 '+1.5 .:3 AD'?12(, 313' '3-D (2) 1 .. ;;. AD129 ! "'1. ~ .:3 AD9123 30'3-D (3)' 1 ". ;;. AD130 '+1.~ .7 AD4 a 2-D 4,. " AD131 ''''1.~ .6 I1D13.) 0 2-D 4,. ,. AD133 a .:3 AD4 a 2-D 4,. ;;. AD134 a .:3 AD133 a 2-D 4 .. ,. AD13~ a •• AD134 a 2-D 4 * ;;. AD13f:i .a .6 AOll5 a 2-D 4,; ;;. AD137 '-0. S .6 ADHS :313' rlQH 1 * ... AD138 !-.).~ .6 AD'?137 30' 3-D 1 "" ;;. AD13'3 '-0.5 .:3 ADH~ 30' t~ON 1 "" ;;. AD14a !-a.s .:3 AD':13', 313'3-0 (1) 1 ,.. ;,; I1D141 '-0.~, .:3 A0914.) 313' ,'3-0 (2) 1 .. ;;. AD 142 ! -2 .';' AD4 a! tNH 1 ... '" AD143 ! -2 , • .; AD9142 a :3-D 1'" ,. AD144 ! -2 ! .6 1101:36.) 2-0 4,.. .. AD14~ ! +2 ! .6 A0131 a! 2-D , 4 "" ~-------!----!---- ---------!--------- ~-----!-------!-------~ ;;. AD141.i ! +2 ! • Ii 4! AD1 .. 5 0 2-D 4;; ;; AD147 !",1. '5! • Ii A044~ 30' HON 1 + ~ ADI4:3 '+1. ~, .Ii AO?122 30' :3-D 1 .. ;; A014'3' 0! • .; AD136 \) 2-D 4,. ;; ~Dl~0! 0! .6 At!4 0 tlON 1,; " AD1~1 0 • .; AD91a7 ~ 3-D 1" ;; AD1~Z 0 .3 A0134 0 2-0 4;; ;; AD1~3 a .:3 • A04 a rh)N 1" ;; A01~4 .) .:3 AD': 11:3 a 3-D 1" ;;. A01~' -2 .6 AD144 a 2-D 4;; '" A.Dl''; -2 • Ii A04 0 NON 1" ~ AD1~7 -2 .6' AD'314~ 133-0 1" ~-------!----!----~---------!-------_-I------!-------! _______ ~ '+ AD1~a -2!.';!3 - 6 I AD144 ! ~ ! 2-D ! 4 '" '" AD1", -2 .Ii A04 , 0 'NON 1;; ;;. A0160 -2 .Ii AD':142 133-0 1'" ... A0161 a • Ii AD131.i 0 2-D 4" .. AO 1 f:i2 a • Ii AD4 a NON 1 .. ;;. A0163 a • Ii AD':1137 0 3-0 1;; ... ~Ul1i4 0 .8 AD134 0 2-D 4'" ... AD16~ \) .:3 AD4 a rl')N 1 '" .., ADI6'; a .8 A09118 a 3-D 1 .. ,.. A0167 +1.5! .6 A044'5 :313' NON 1;,; ;,; A016:3 +1. S! • .; AO',122 30'3-0 1 '" ,.. AD16'; +2'.'; AD1"'5;a 2-D 4" ~~~~*.+~ ~~~~*~~~~~~*~~~~~~~~*~~~~~~~~~~~+.~~~~~~~+.~~~~~~~~~~~~

30

Figure 2

Rows of recorders 1-4

r--------------------------------------------------, I NON ADA PTE I

~--------------------------T-----------------------~ I Incidence I Mach I

~----------~---------------+-------~-------T-------~ I AfHchee I Aerodynanlique I 0.6 I 0.' I 0.8 I

~----------+--------------- ~ I I +1.5 I +2 14' I I

~----------+--------------- -------+-------+-------I 0 I 0 150 I I 153

~----------+--------------- -------+-------+-------I -2 I -2 156 I I l __________ ..1 __________ • _____ "-___ ... ~L.. ____ ~ ___ -'

r--------------------------------------------------, F~OAPTE 3-~


~----------~---------------+-------T-------T-------4 I Affichee I Aerodynamique I 0.6 I 0.' I 0.8 I ~----------+--------- .. -----+_---~---__t---_I I +1.5 I +2 148 I I

~----------+--------------- -------+-------+-------I a I 0 151 I I 154

~----------+--------------- -------+-------+-------I -2 I -2 15' I I L __________ ..1 _________ •• _____ ...... ___ --li. ____ -"-___ --'

r--------------------------------------------------, I AOAPTE 2-D I

~--------------·-----------T----~------------------4 I Incidence I Mach I

~----------~---------------+-------~-------T-------~ I AfHchee I Aerod~:'"atnique I 0.6 I 0.' I 0.8 I ~-.---------+---------.------+_---+----+_--___t I +2 I 146 I I

~----------+--------------- -------+-------+-------I 0 I 149 I I 152

~----------+--------------- --- ..... --4-.... ---.---+-------155 I -2 I I I l .. _________ J _________ . ____________ .L ____ .... ' ___ --'

Affichee - Displayed

31

Figure 3


r--------------------------------------------------, I NON ADAPT! I


•. ----------'T-~-------·-·----':"+-------·r-------'T-------~ I Affichee I Aerodynamique I 0.6 I O.? I 0.8 I I. __________ +---------·-·-----?-----JI-----+-'----t I I +2.17 121 I I

I ·2 ~--------------- -------.-------+-------I I +2 120 I 1

~----------+--------------- -------+-------+-------I +1.5 I +2 122 I 124 1 126

~----------+--------------- -------+-------+-------I 0 1 0 10?' I 105 I 109 I I 109 I I 132

~----------.--------------- -------.-------.-------I -0.5 I 0 13?' I I 13~

~----------+--------------- -------+-------+-------I -2 I -2 142 I 110 I L __________ .L ________ • _______ ~ ___ .01.' ___ .....1 ...... __ .....1

r--------------------------------------------------------, I ADAPT! 3-D I

~--------------------------'T-----------------------------4 I Incidence I Mach I

.----------'T---~--------~--+-------T----------T----------~ I Affichee I Aerodynamique I 0.6 I a.?' I 0.8 I • __________ +---------------LL I I 12?,(1) I +1.5 I +2 123 125 128(2) I I 1 I 129(3)

.----------+--------------- -------+----~-----+----------I Q lOll?' 1 115(1) I 118(1) I 1 I 116(2) I 119(2)

~----------+--------------- -------+----------+----------I - 0 .5 I 0 138 1 I 140 ( 1) 1 1 1 I 141(2)

.----------+--------------- -------+--------~-+----------1 - 2 1 - 2 143 1 I l-~---- ____ J. _____________ • __ ....... ___ _:lIIoo...----..... -----..J

r--------------------------------------------------, I ADAPT! 2-D I

.--------------------------T-----------------------~ I Inc idence 1 Mach I

.----------T----------~----+-------'T-------'T-------~ I AF Fichee I Aerodyrlamique I 0 .6 I 0 .?' I 0 .8 I • __________ +_______________L I +2 I . 145 I I

.----------+--------------- -------+-------+-------I +1.5 I 131 I 130 1

.----------+--------------- -------+-------+-------,I 0 I 136 1 135 1 134 .----------+-------_._._----- ------.-+-----~-+-------1 -2 1 144 1 I l __________ J_______________ I

32

Rows of recorders . . 3-6

r--------------------------------------------------, I NON ~D~PTE I ~-----------------------·--T-----------------------4 i Incidence I Mach I

~----------T----------··----+-------T-------T-------~ I Affichee I AerodynamiqQe I 0.6 I 0.' I 0.9 I ~---------- ~-- --------.. ----+----I-----f----i I +1.5 I +2 16' I I

.----------+--------------- -------~-------+-------I a I 0 162 I I 165

.----------+--------------- -------+-------+-------I -2 I -2 159 I I L __________ ..l __________ •• ____ .-____ .. ____ ~I ___ _'

r--------------------------------------------------, I . ADAPTE 3-~ I

~--------------------------T-----------------------4 I Incidence I Mach I

~----------T--p------------+-------T-------T-------4 I Af fichee I Aerod~n~LmiqQe I a .6 I 0 ., I 0 .8 I ~-- ___ -- ___ I _______ - .. ___ -- _ +-____ ',.11-___ +-___ -; I +1.5 I +2 168 I I

~----------+--------------- -------+-------+-------I 0 I 0 163 I I 166

~----------+--------------- -------+-------+-------I -2 I -2 160 I I I. __________ J. ________ •• ______ ....... ___ .... I ___ ---i"--__ ~

r--------------------------------------------------, I AD~PTE 2-D I

.--------------------------T-----------------------4 I Incidence I Mach I

.----------T---------------I-------T-------T-------4 ~ Affichee I AerodynamiqQe I 0.6 I 0.' I 0.9 I !~----------+--------.-------+_----_f'------...._I---._; I +2 I 169 I I

~----------~--------------- -------+-------+-------I 0 I 161 I I 164

.----------+--------------- -------+-------+-------I -2 I 158 I 1 L __________ ..l ________ . _______ .-. ___ ... ' ____ ..... ' __ ___

Affichee = Displayed

Figure 4

33

Figure 5

Presentation of mounting

34

WING MOUNTING

FIGURES 5 TO 13

35

w

""

~~~"",,,~~,>;»» > "----------f-------..... > '> '> i> :> '> I , ... - __ - ___ _

x

y

~

----.,----

Wall ref. j

w W .f'-

7 > 7 7 7 7 7 7 7 7 17 7 7 7 7 7 7 7 777 7 7 7 717 7~ c

~

ro Diagram of wing mounting

""

W --..J

'.L..-

v ~

I

--- -31 31 • " 'l ~ 'I 'J t'ia;;;'!fJ~ft'" " .a f4 " tr. -~ .. _- --4-- i6 e- • I .. - .. e -

n 3l 31 2lt7 III U 11 11 i7 t, ij tJ' H!!:H 1'1 iI f2 i4 i' i! III it ¥ fa 2 1 B' ..... -...-..---... ~ • ....--. - ~ ........ .., .... .- - 01

34 U 30 21 26 24 2t 20" 16 l' 11 10 a 64 1,1 n 7 i I 13 i .-7. i 21 nT FJ: ~ -: --. · ' .. -.-...:..- -...- • ---e. ~~.Ji •• -'-. ~- --: - .-

_ II - f - 'l '1- ~ ~t ~, 'l _ ~ _ ~ _ 20 . -~ .

100

L. I

-- -

0 -N -..t

395

1430

I .-1. , !

-r+1 -

! j~ JUL f---i ib -- r-fi

,

18 b

375

l Beginning of door

End of convergent

r 50 ---,

.. i+. _ "i -- ~ K 0_ -\~il!& - - N

21 -to --;.,- . 50 J

•• I 180

-:!I5 3$ I

Section axis End of door

Diagram of wall pressure recorders

I%j ..... lQ c 1"1 ro '-J

Figure 8

Equipment of adaptable cryogenic walls: specs of pressure recorders, jacks, and thermocouples

Wall pressure recorders Jacks --

I }~PH XP8 ZP I ~~?H ):F'8 ZP I 1,)1' (",','

1 -812.5 -812.5 213.13 4'~ 2613.0 260.13 213. ~3 1 ·-i'05.1:J

2 -787.5 -737.5 -213.'3 59 2.,e.eI 2913.'3 -2(1.13 :2 '-575.0

3 -747.S -747.S 20. ~J 51 3313. a 33'3.'3 20. ~3 3 '-460. ~3

4 -722.5 -722.5 -213. ~3 52 :;::na. '3 ~::3~J. 0 -2'3.'3 4 ·-~:55. ~j

5 -692.5 -6n.5 2e.~ 53 417.5 417.5 -2~3. '3 5 -·275.13

tS -657.5 -667.5 -20.la 54 442.5 442.5 213.0 6 "215.0

7 -63a.~3 -638.13 -2'3.13 55 467.5 467.5 -2~3. '3 7 "155. e

:3 -592.5 -592.5 28.a 56 492.5 4'32.5 2a.~ :3 -95.9

9 -567.5 -567.5 -20. ~3 S7 517.5 517.5 -20.'3 9 -35.0

11:'1 -5313.13 -530.13 -28. () 5~ 542.5 542.5 213. ~3 10 25.13

11 -492.5 -492.5 28.0 53 -630.0 -63~3. '3 2~3. '3 11 85.13 12 -467.5 -467.5 -2e.() 60 -5313.8 -5313.13 20.'3 12. 145.13

13 -442.5 -442.5 28. ~I 61 3813.9 3S~.'3 28.13 13 2t1S.0

14 -417.5 -417.5 -28.0 62 -735.8 -735.0 -133.0 14 285.13

15 -:332.5 -392.5 28. ~} 63 -530.8 -5:313. a -133.1} 15 330.0 16 '-367.5 -367.5 -28.0 64 -33'3.13 -330.13 -133.~3 16 505.13 17 '-338.0 -338.'3 221.121 6S -288.13 -2130.13 -133.'3 P --2::13.13 -298.13 -29.121 66 -1~1:3.13 -1£lI3.a -13:3.~3

'J

1 " --2613. ~ -268.'3 213.0 67 -4'3. ~3 -413.13 -133.13 21) ·-23'3.0 -230.9 -213.0 68 a.a 13.0 -133.(} 21 '-2138.13 -208.13 213.13 69 4a.0 4~. ~3 -133. ~3 THERM. :22 --178. a -178.0 -2a.~ 713 lea.e 1013.'3 -133.13 ... ***io* "',' "145.13 -145.£1 2El ;·13 71 213a.13 20'3.£l -133.~ ,;,.J

24 -'128.0 -128. ~3 -213.0 ~ . ., 3313.0 ~:3e. e -133.'3 t ...

25 -·Hla.~3 -HI0.e 213.0 73 538.13 5313.0 -133.0 I ><TH "'- -85.a -85.13 -28.13 74 -735.13 -735.13 133.Q ..:.::. 27 -78.13 -713.0 28.'3 75 -€-38.'3 -639.8 133.13 8 -~~3? '3 23 -55.0 -55.13 -28.13 76 -5313.13 -530:9 12:3. I) 7 0.13 29 -413.13 -4e.a 28.a 77 -439.8 -4313.13 133. '3 9 475.13 39 -38.13 -38.0 -28.13 78 -3313.13 -33'3.13 133.13 31 -213.8 -213.8 28.0 79 -260.e -2613.0 133.0 I :r.:TS 32 -10.13 -18.13 -213.13 8a -2al3.a -21313.8 133.13 -:") 13.13 8.a 213.13 81 -145.13 -14-5.13 133.13 6 -7'37.0 -.. "J

34 la.a 19.8 -213.13 az -1813.8 -11313.0 133. ~J 4 -427. ~) ~:5 28.13 29.0 28.0 83 -713.13 -7~.~ 133.0 2 -1813.~J

~:~ 30.13 38.13 -28. ~3 84 -48.0 -413.13 . 133. a 1 ~.~

37 43.0 413.8 28. 13 8S -28.a -29.13 133.'3 3 17'? I) ~,~ 55.13 55.13 -Z8.e 86 '3. 13· a.e 1:33. ~3 5 479. ~J " .. "J

39 70.0 7'3.8 za. ~3 97 Z0.e 213. ~3 1:33.13 .. P3 78.8 78.3 -20.13 88 48.13 413.13 133. 13 41 91.3 91. 3 28.0 89 78.13 7e.e 133.0 42 laa0.0 100.\3 -213.'3 9'3 lee.a 10e.'3 133.1) ...... .,..,:, 123.13 12e.0 28.0 91 139.8 133. a 133.13 44 ll38.8 138.8 -2E1.13 92 200.13 20~3. 13 133.0 45 151.3 151. 3 28.8 93 260.13 269. ~3 133.13 46 ],70.13 178.13 -213.13 94 3313.\3 nO.a 133.13 47 &:013.13 28e.a 28.13 95 430.0 430.13 133.13 43 2.30.13 2313. a -zEI.a 96 538.13 539.13 133.13

XPH-.XPB-XV-XTH-XTB IN MM/AXIS PORTHOLE Z in mm/section axis

38

Figure 9

Pressure recorder sE§cifications - lateral walls (mm)

upstream hole central hole N I X Z II N X I Z

----1----- -----11---- -----1-----1 I +15Q II 2 1-375 +100 II 3 I + 50 II

----1----- -----1 4 1-455 I 5 1-410 1 6 1-375 0 I 7 1-335 1 8 1-295 1

----1----- -----1 9 1 - 50 I

10 1-375 -100 1 ~ 11 I -150 I ~ ____ I _____ ----_I

1 1+160 :2 0, 1+140 :~ 1+120

----- 1-----, 4 -120 1 5 - 80 1 6 - 40 I , 01+100 EI + 40 I 9 + 80 I

10 I + 12 0 1

----1-----1-----11 1 1+ eo 12 1 0 1+ 60 13 1 1+ 40 14 1 1+ 20

-.--- 1-----15 1-160 16 1-140 17 1-120 19 1-100 19 1- 80 20 '1- 60 21 1- 40 22 - 20 23 0 24 + 20 2S + 40 26 + 60 27 + 80 28 +100 29 +120 30 +140 31 +160

o

1 .1

1 -----1

32 33 34 35

36 37 313 39 40 41 42

o

-120 - 80

1- 40 I 0 1+ 40 1 + eo 1+120

--.. - 1-----4:~ 1 4'1 1 0 4c' •• 1 ___ ._ 1 ____ -

- 20 I -'40 J - 60 - eo

-100

-120 -140 -160

downstream hole 1 N X I Z J 1---- -----1-----1 1 1 1+150 1 I 2 +375 1+100 I I 3 1 + 50 I 1---- -----1-----1 1 4 +295 1 I 1 5 +335 1 1 1 6 +375 I 0 1 I 7 +415 I I 1 e +455 I I

1---- -----1-----1 I 9 1- 50 1 I 10 +375 1-100 1 1 11 1-150 1 1 ___ 1 1

39

Figure 10

Diagram of the win~

AS07

4

-E E ...,

N 3

4110

2 -20

1

0 ..

0 X (mm) 0 .. .. 40

Figure 11

Specifications of the AS 07 wing

A B.A. B.F.

I Y I X I ,< 1 corde I (rom)

------------1---------1---------1---------1---------1 B _::::~::~~~_ : ____ ~ ____ : ____ ~ ____ : _~~~.::::_: _:~~~:::_: c __ ~~::~~_~ __ : __ ~:~:~ __ : ___ ~~~~ __ :_:~:~~: __ :_~~~~~~ __ :

ra"qee 2 1 30,34 1 17,88 I 146,12 1 128,24 1

------------1---------1---------1---------1---------1 ra"qee 3 1 60,40 1 35,6 1 144,15 1 108,55 1

------------1---------1---------1---------1---------1 I:'tlpttlre 1 75) 227 i 44,335 1 143,18 1 98,845 1

------------1---------\---------1---------1---------1 ra"qee 4 1 104,301 1 61,47 1 153,61 1 92,14 I

~-----------I---------I---------I---------I---------I ra"qee 5 I 196,41 1 115,75 1 186,66 1 70,91 1

------------1---------1---------1---------1---------1 ra"qee 6 1 279,87 1 164,94 1 216,60 1 51,66 1

------------1---------1---------1---------1---------1 J) :iatlmo" 1 309,60 1 182,464 I 227,264 1 44,80 1

---------------------------------------------- ______ 1

Key

A - chord B - root C - row C - tip

41

• &0

FigurE~ 12

u , N

Key

Position of pressure recorders for each section

A ~~ __ ~~~~ ____ ~_~~~~~ __ ~ ___ ~_~ ______________________________ : B 1 Extrado~ 16 pri5e5 1 3 5 8 12 16 20 25 30 % 1

1 1 35 40 50 60 70 15 80 90 \ 1

I----------------------------~----------------------------I t 1 lntrado$ 9 prie.es 1 3 7 15 30 45 60 75 85 \ 1 1 ___ • __ -----------------------------------------------_______ 1

Profiles

-------------------== -..- -=::::

A - B.A. 1 recorder 16 recorders

8 recorders B - Outer section C - Inner section

42

Figure 13

~pecifications of pressure recorders on "Airbus" AS07 wing

10 25

'~.- -=+ • I

r-----------------------------------------------T~-----------~----------------------------------,

t--------.- --fl--T ~~ ~~ -~ -~::~ ~:~ -T ---------------1-------____ IJ. --T ~:~~- --~::~::~-T------------ --- ~ co I range,. 1 I rango. 2 I rango. 3 I reng... 4 I r • .iv..:1 I ranIJ.. 6 I

I V - 7.:l60~m I Y - 30.340m. I Y - 60.400~~ I Y -104.301 ••• I Y -196.410 .. I Y -279.870-. I I---------------~---------------~---------------~---------------~---------------,---------------l

J) IB.A.- '1.295,"" IB.A.· 17.715 .... IB.A.· 35.498", .. IB.A.- 61.392." .. IB.A.-115.701 .... I.B.A.-114.143_ I f IB.F.-147.620m .. IB.F.-l'16.120"". IB.F.-14'1.150m .. IB.F.-153.610.nm IB.F.-186.66o.". IB.F.-211.600.". I ~lcordoI43.160m .. IcordoI29.2'10", .. Icordol0B.550 .... Icord" 92.1'10'010 Icordo 70.910 .... Icord. 51.6600". I

I X hom) I Z (mm) I X (m .. ) I Z (mm) I X (mm) I Z (10m) I X (mm) I Z It.m) I X (mm) I Z ( .... ) I )( It.",) I Z (.".) I

r .. -~-------~-------,-------,-------,-------,-------,-------,-------,-------,-------,-------,-------l 11125.9791 -1.0601126.7531 -.9121127.7'1'11 -.4771139.7961 -.4271176.01'11 -.5291209.8021 -.6111 21111.6521 -2.0301113.9'161 -1.6031116.B601 -1.1041130.5461 -1.0591169.8831 -1.0621203.6551 -.9401 31 90.2251 -3.3931 94.6431 -3.0431100.6961 -2.3491116.6091 -2.0471159.1921 -2.0951195.9771 -1.6861 41 69.7031 -4~1001 75.4761 -4.0261 84.4441 -3.4161102.910) -2.9411147.6761 -2.9361188.1101 -2.24'11 51 47.0661 -2.6701 56.0691 -3.4111 69.0841 -3.1551 99.0961 -2.6831137.0291 -2.7391180.3791 -2.2341 61 25.7418 .8331 36.7851 -1.1561 51.7531 -1.6801 75.2791 -1.4041126.'1441 -1.9331172.7751 -1.6851 71 14.6241 3.7941 26.5601 .9241 43.0911 -.1991 67.9091 -.3441120.6611 -1.1601169.5321 -1.1591 91 8.7511 5.7831 21.2491 2.3951 39.9731 .8691 64.1741 .4591117.7681 -.5311166.4871 -.7421 91 4.2951 10.8001 17.7151 6.3271 35.4981 3.9231 61.3921 2.9091115.7011 1.3021164.9431 .6311

101 8.7231 15.4931 21.7701 9.9861 39.9401 7.0701 64.2671 5.4671117.9731 3.3231166.5471 2.0251 111 11.5951 16.1991 24.3581 10.4871.41.1051 7.4961 66.1081 5.9431119.4171 3.5991167.6341 2.2031 121 15.9461 16.6471 29.1291 10.9231 44.2831 7.9491 69.8971 6.1101121.5011 3.8351169.0651 2.4421 13121.6181 16.6041 33.2521 11.2531 4b.6401 8.1841 72.6441 6.4091124.4221 4.0571171.2781 2.6761 141 27.2771 16.4891 39.4121 11.5291 52.9g11 9.3151 76.3131 6.5991127.2901 4.2571173.3751 2.8091 151 32.9111 16.2591 43.5671 11.6341 57.3g31 8.4901 80~0391 6.7451129.9931 4.3201175.4301 2.9221 161 40.3451 15.8321 50.1301 11.6211 62.7711 9.5391 84.7001 6.7841133.4731 4.4401177.9311 2.9541

1171 47.3781. 15.3251 56.4151 11.5521 68.2031 8.5991 89.2201 6.73111137.1561 4.4991190.6421 2.9741 1181 54.6001 14.7791 62.3671 11.3731 73.6291 8.5591 93.7971 6.6741140.6191 4.4421183.0361 3.0241 1191 61.8171 14.1091 69.2751 11.1231 79.0511 8.3301 99.3531 6.5571144.2141 4.4391195.8511 2.9851 1201 76.0801 12.5931 81.9701 10.4771 99.9051 7.9861107.6211 6.1191151.2501 4.1161190.9361 2.8621 1211 90.3931 10.9711 94.8431 9.2691100.7071 7.1621116.9091 5.5641158.2431 3.8241196.0001 2.6491 1221104.7291 8.9911107.7031 7.9231111.6691 6.0901126.1681 4.9141165.5011 3.3311201.1001 2.3121 1231111.8391 7.8691114.0701 6.9611117.0011 5.5601130.6411 4.3111169.9271 3.0091203.9411 2.0561 1241119.0201 6.7011120.4921 5.9801122.4671 4.9461135.2041 3.7471172.3671 2.6291206.3491 1.9501 1251133.2691 3.9201133.~)11 3.6261133.3041 3.0711144.3551 2.4271179.5521 1.6941211.6141 1.1811 L __ l _______ ! _______ , _______ £ _______ ! _____ •. _~ _______ l _______ ~ _______ ! _______ ~ _______ ~ _______ J _______ J

A Internal wing B External wing C Row D B.A. E B.F. F Chord

43

CONTROL TESTS

Wall incidence and rotation:

Convergence of iterations:

Non/2-D/3~D comparison:

Figures 14 to 16

Figures 17 to 20

Figures 21 to 23

44

A - Non-adapted B - Wall shapes C - Row D - Upper wall E - Lower wall

Key to fi~res 14, 15, and 16

F - Central rows of pressure recorders

45

,

I. M=O.6 .

"0120 I a. =+20 A0122

,._, J

• ~ ~ 1:

A non ada pte

0_ AD120 ::0 0

• te::....- I : • __ AD122 . rt OJ rt

18-::J .. I"%j 1-'-

-I' I

l .. ~~--~_t"1

.70T I , I· • I . m

rt

U I c: Rangee@ ()

«

I I~ •• 11. 1: Parol haute D

I-'

•• 0. s.-. ........... ...-n .... ~ x/c • ••

Paroi basse E I ~ ~ ~ I

- . .lIsl

Rangees centrales de prises de pression F

X (mm) I"%j

• 1101 I I I 1-' •

v 0 9 0 lO .C) 0 0 c 0 II 1\ t"1 .. I I CD

~

0"1 I-' ~

•• 0

.. " •• 0

• 7.

.70 0 0 0 ..

~

-....J

I.

•

o

-.. I

A0108

A0139

.B Formes des parois

a.e

~- .. .... ....

I.e

"

, , , , , .... .... ............

M=OI8

0.=00

A non adapte

0_ AD108 + __ AD139

Rangee@

C.

:u o rt' \11 rt' 1-'. o ;:!

I··

til (!)

o o :::s 0..

I , " XP U 0 I « 0 f: :!: I .•

... 1 Il I I

" X/C

£ Parol basse

F Rangees centrales de prises de pression

X (mm)

0 0 0 0 0 II II I

~ ~ ~ ..

~ 1-'. lQ C ~ It>

I-' VI

" '" ;

01:>0 CO

'0 Tn.. "N /'

. ~-• .c......

-.. ... ~ '·°1

•• 0

o Paroi haute

~ ........ L ._ ~ -;~~.~

• £ Paroi basse

~AD119 AD141

B Formes des parois

o 1

••• Itt

II \,,_

.. .11 ~----

..

\ M=O,8 \

L?-::~c , A adapte 3_D

0_ ADl19

+ __ AD141

c.. Rangee@

1-3 !:J" ..... 1'1 0..

(") o

...I I~/c ~ ~ ~ r •

.'7. F Rangees centrales de prises de pression

X (mm)

• '701 0 o 0

g f .. •

0 0 0 a

I ..

~ ..... lQ C 1'1 CD

~ 0\

_.

First case

•• Il. A , N Form" des parolS

•

o

•• 0

• · • I

.J X

\ C. • If!\ ' Rangn \¥I

-L ".. \

XP

: •

0_ AD 105 (0) • ___ AD 115 (1)

• _, AD '16 (2)

_ •••• AD9116 (3)

\::::: ==.::::=:-:.:::::::::::::::;:;~:::=== ------- --O::::::::::==~~

..

....... ----~ I ~ •

!5~

A - Wall shapes B - 3-D convergence, no rotation C - RO\lI

x/c

Figure 17

49

.e Il N

e

e

.. •.• J-_____ _

~ .

Kex.

A ... Wall shapes B ... Row

o o • I

Second case

•

XP

: • o : CI_ AD 126 (0) • ___ AD 127 (1)

._. AD 128 (2) .• __ AD 129 (3)

• ____ AD9129 (4)

X/C . ~

FigurE? 18

50

A - Wall shapes

1.1

I.'

.'

..

•

c. ~ Range.®

'\.

o o 1

• o . •

Sans rotation

XP

: •

\ \. ~~-~. ~-;;:~~.-~.~~

~;,--- ~-....::: .. ........-;;:: ~

. . ---=::----==--.D

AD133 (depart A04) • _ iteration (0)

(1)

(2) .. (3)

x/c .,.~----"""',----------"!--_--"'"

I ~ ~ ~ ~ .; -

B - 2-D convergence, no rotation C - Row D - Beginning

Figure 19

51

1.1

..

1.1

: •

Key

I.

•

•

-10

A Q. Forme-s dH porois N

~

o o . I

A - Wall shapes B - 2-D convergence, no rotation C - Row D - Beginning

~

o

! M=o,a! --~ a=Qo

.B Conv~rg~ncl! 2-D

Sons rototion

XP

g . g •

j) A0134 (depart AD133)

0_ iteration (1) (2)

._. (3)

.__ .. (4) x/c

, ~ ~

Figure 20

52

A - Wall shapes B - Row C - Upper wall D - Lower wall

Key to figures 21 and 22

E - Central rows of pressure recorders

53

Figure 21

Non/2-D/3-D comparison

..,...,. ........ _---.... ,.:....-_ --·---AO\35 2-0

,,.,-:;"/ _. __ ~ ... ADI05 non "l:!t .. .".--~............. .~ . .~ - , "'AOll6 3_0 '.0

. A FormH d~s porois

.Ia.

.[.~T~ .. --....~,.

~ ... -I. f !

,

:r u «

, .va :r

• vo

.11.

XP -

..

•••

..

..---~~~~---- =--::.B Rong.~ <Z>

----_ . B Rang •• C5> ............. ---=:::::::::::

__ AD105 non ada pte

• __ AD135 ada pte 2_D __ . ADl16 odopte 3_D E Rang."s centrales d" pris". d" prllssion

X (mm)

eliOt'"" -- '--;:-----.... , ----.:.. ..

. ~ O! O.O;-____ -m ___ ~~-------~H~/:C

: m ~ ~ : ..

54

...

I I

Figure 22

Non/2-D/3-D comparison

. c., A FormH des parols

~~ ....... ...

~ -.. . .......... , , ! - XP • i

I , Rongt.s c"'lro~s de prlsn de pression

X (10m) I • -<

I

..

~:---:Jlr----;r' - ___ --- )(/C

~ ~

'.0

..

111.0 o o .;

)(/C -.:

55

o

-,

/2 -D/3-D corn Non parison

non . LD tat ion . __ _

Adap . 3_D

-~ O· "CSence: 1nc.

. .: 0,8

3

:> X (mm)

!

• •

:

Figure 23

®

.@

®

56

VISUALIZATION OF CURRENT LINES

ON THE LEFT LATERAL WALL

Mo = 0.6 oL. = +2· Non-adapted Figure 24 Mo _. 0.6 cl.. = +2· 2-D Figure 25 Mo - 0.6 01-= _2· Non-adapted Figure 26

57

Figure 24

Left lateral door visualization ~= +2· M = 0.6 non-adapted

58

Figure 25

[illegible]

59

Figure 26

Left lateral door visualization ~= -2· M = 0.6 non-adapted

.. --- :=:3 - -~ .. - -.

--=;. -

60

Use of four base cases

o

H-O ,6 0,8 .----------.

147 (*) 122 (**) 1 167 (***) 1

----------1----------. 150 (*) 1 153 <*) 1 107 c**) 1 lQ3 (**) 1 162 (***) 1 165 ( ;,**) 1

----------I----------! 136 ( .... ) 1

159 (***) 1

----------!

H-O,6 0,8

1 1'46 (*) 1 +2 1 1~5 (**) 1

1 B~ (**"'ll

I----------I---~------. 1 14:: C*) 1 152 (*) 1

a 1 136 ( ... *) 1 134 ("'*) 1 1 162. <***ll 164 (***) 1 I----------I----------! 1 155 <*) 1

- '2 1 144 < ** ) 1 1 158 (***) 1

!----------! H-O,6

1 148 (*) 1 "'2 1 123 (**) 1

1 1S:3 < ***) 1

0,9

1----------1----------. 1 1S1 (*) 1 lS4 (*) 1

o 1 11 7 ( ** ) 1 119 (**) 1 1 163 (***) 1 lSS (***) 1

I----------I----------! 1 157 <*) 1

-2 1 143 <**l 1 1 lSI) (***) 1

!----------!

Shape of walls Mach on adaptable walls Mach on lateral wall Kp distribution Lift coefficient

NON ACAP,.E

<*) ranqees 1-4 <**l rang~e$ 2-5 (***) ranqss3 3-6

AD~P"E 2-D

ADA?1'E 3-D

Figures 27-28 Figures 29-32 Figures 33-36 Figures 37-44 Figures 45-50

Figure 26a

61

Use of the four base cases - Wall shape

,0

-::

o

-.0

o o . I

o : I

a. N

a. N

; I

: . I

~~:::::=::;;:~:- 1.0144 adapW 2_0 ~ 1.0142 non ada pte

1.0143 adopW 3_0

-""'-It.::;;;::;:::;:::::,;;;::.:=-_ sans rotation

XP

i AD 122 non adapte

• rotation 30'

- • rotation 30'

------------ so.ns rotation

o o :

XP

o o •

"Sans rotation" = No rotation

Figure 27

62

Use of the four base cases - Wall shape

I.

•

• : . I.

•

•

I I

n. N

n. N

I MoO.S! a.= o·

o ~ •

! Moo.a! a.= O·

! I

"Sans rotation" = No rotation

-..........

•

•

--""

adapte 2_D non adapt.

-...... sans rotation -..... XP

• t • o .

: •

Figure 28

63

Key to Figures 29, 30, 31, and 32:

A - Left lateral row B - Central row C - Right lateral row

64

Figure 29

Use of the four base cases - Mach of adaptable walls

.70

... -"

A0142 non odopte .BB

x (mm) .. 0.1------_, ___________ _ g o i ...

•• 0

....

I U ~ 1:

o

A •. ... rangre klt«alI! gauc:hl1 ~ . _ rangre c~rQIe '- ••• rangH Iat~ droit.

_ ... __ ............ : .. : ..• ,~ •• --4~~

A0144 odopte 2-D

x (mm) •• O'~ ________ ~, _________ ~ ____ • _____ __

... .80

o o ~ •

.BB

o o ~

t' •.... ·a ....... ~ .......... ~

x (mm) .H,~-----___ -.· __________ ~----------~

g o .. •

o g •

65

Figure 30


•• 0 ~ - .... . .. -,,'ft······ ... ~~ ... ~. -'" .

A0107 non odapte ... x (mm)

.~--------~.----------~----------~ .110

0 0

~ •

•• 11

I U ~

•• 0 l:

.1111

.11

0 0

~ • ....

I U ~

.110 l:

."

.110

0 0

~ I

o , o

A ... " fClngH IateraJe gauche B ' - rangH cmrall? c... .- - rangH laterote droit.,

• » .. ~

----...... "icd! .. ~~~ Iait

CI CI .. •

-

g II I

o

o

A0136 odopte LO

x (mm)

o o ..

AD117 odopte 3_0

x (mm)

66

Figure 31


.70 I: U I M=o,61 < ... l: a=+2°

•• 0 >. o~ .. 'O

• ell AD122 non adapte

X (mm) .eo ---1

0 0 0 .. 0 0 0 ~ , IS I

A 0000 0 rQ~ Iat«CIIe gClUClw . .., 5 0_ rQngH c:.ntrQ( • I: C ._- rQngH tat.rcu. droit. U « ~. .... l: "'.~ ,... = ....... ~.......=;4:::c.~

--~- - ...

A0145 adapte 2_0 .eo

X (mm) ---1

0 0 .. 0 0 0 0 ~ • IS I

I

... I: U « ~ l: >- .... ..., .... '

•• 0 ...... ~ ... -: . ,', .. . ' ....

A0123 adapte 3_0 .... X (mm) .... -

0 g .. 0 0 0 0 , • .. I

67

Figure 32


." r u < ... l:

•• 0

AD108 non ada pte .'111

X (mm)

.'10

0 0 0 0 0 0 0

~ II II

• • • •..• ~~~g~

.. 8. . _ rangft c.ntralf

r • __ rangH ~alf droit~

U < ~ ......

•• 0 l:

" .. -'

A0134 adapte 2-0 .'111

X (mm) .'10

0 0 0 0 0 0 0 ~ II II

• • ... r u c(

.110 l:

A0119 adapte 3_0 .'1.

X (mm) .'1

0 i II II II 0 : I • I

670..

Key to Figures 33, 34, 35, and 36:

A - Vertical rows D upstream

middle downstream

B - Horizontal rows o upper

middle lower

68

Figure 33

Use of the four base cases - Mach of lateral walls

.70 I Or? u ...... <{ E 1: .§ ...

>-

" . _TfjQ5 MAC~ · . . · . · . · . · . • eo ~-- AD142 non adapte

.70 1: I U'E <{ E

•• 0 1: ....... >-

X (mm)

o

I~-TMAC~ . . . . .. . 15

RangHs yfliica(H

• Qmont m~iQ~

• aval

•• 0 ------.----- AD144 adapte LD

X (mm) .M.~------_________ ~

o ~ I

'70I~ I~ <I: E .•• 1: !

>-

o o o •

MACH Tfi

~~ horizonta(ps

• SUPffNH __ rMa.anps

inf'rleurH

.eo ~-- AD143 adclpte 3_D

X (mm) --, o I

69

Figure 34


0rlS ~j~~ __ ~ __ ~_M __ A.CH .10 :r •

u ..... • « E • ~ E •

M=O,6 a=oO ... ~ ...... .

.~

~ ....... ~--•• 0

x (mm)

"

.10 I rTl-: U E . « E :

.ID l: >-

I I •• 0 ------~.~.~~~------""

x (mm) .... 0 0 " II I

AD101 non ada pte

MACH A

B9.!lg~ ...rtic:al.,

• omant ~ian"

• avaI

AD 136 adapte LD 1> 8,gngHs horizontal.,

• superMoutH _ median"

• inf.rieul'H

MACH

'7°1~ I~ ... 1:

~

~--'--I "!----I'

.... ~ AD117 ada pte 3_D

X (mm)

.HO~----------~ .. -----------~I , I

70

Figure 35


.?o:rOr' l~ u ..... • < E • 1: E • . .a;: .: r 7

MACH

.80 ~2~ AD122 non adapte

x (mm) • 50 oJ-__ ---:-.-----I~

f :

____ ---,_-,-....:...M:..:..;,A C H

]rIG I; >- •

x (mm)

.lIe.l------- t o .. 0 o 0 o • I

,..._---,_~-M:...:.:A. CH

·"~~r 1/ .... :r >-

A 8£ng.es vertical.s

• amant m~ianH

• oval

RangHs horizantal!!s

• sup.r ieures _ m~ianH

• inf.rieures

•• 0 ______ ~ AD123 adapte 3_D

x (mm)

.DD~-----_·----_I gog ,. .

71

Figure 36


AD108 non ado pte

x (mm)

.711 - -.. .. .. .. .. • • I

MACH Rangm ".,-tical.,

.... 5~1 I • amant rMdianH

< E . oval 1:

..... .

." >-

.... ~~~. A0134 adapte 2_0 8.9.!lgm horIzontat.s

X (mm) . sup~i.ures _ m~iQn.,

.711 --.. I .. .. .. inferi.ures .. .. . • • I

·MACH .... ~~1 f . -1: .....

>-

.... --------~ A0119 adapte 3_0

X (mm) . .,. - I .. .. .. I .. I •

72

o

o

.,

Use of the four base cases - Kp

•

:0,6

• o

....... -

•

non

•

t\.. •.•.•••• _ '.

o '. '. '.

• •

AOt42

"'" )( . .. ~~. -F--':::"':':':-':':'" ~"'_' ---...... AOt56

'. o

...... )( c .......

o : AOt59 c..... ____

......................

"" "'1.--....... )IE c .........

• ~ ..... -••. ,....; .. ~ .• ;;:.--== ...... -.::____ AOt42

................ ~ "..... )(

--.-.... --.--.. ;:.. .. -=:~----"""""'--j""'---

AOt56

)( I

-~ X (mm)

Figure 37

®

®

73

_&


&

non ~daptet1on 2_0

3_0

~ 2· incidence: -co

~ech : 0,6

o

o

•

H--------~ S;;;;; ==:-:

x (mm)

)(

!

)( I

:

. ..

:

Figure 38

®

®

®

74

.,


p.dl!lptetion non

,.-inCidence: O·

HOC" : 0,6

o

o

• +-----..:...-.:,~)( @) I

_____ .--:----. AD 107 ......... ... ........ - ~

.•.• .....)IE @ ............ \::::::!.J .. ..

"'-'-"'" ~0150 ............ ,,'" .................... ..

............ _-.. @

_ .•.... ----------... _------........•........ -----.... -.......

A0107

)( ® • :

A0150 .. --------------_ .. --_ ............. _ ... j.:----: • • ..

-~ X (mm)

)( I

Figure 39

75

.&


non

Ad e ptet10n 2_0

: 0,6

o

o •

3_0

o

•

o :

)(

• :

)(

• ~

)(1

!

x (mm)

:

)0(

.. ..

)0(

• •

Figure 40

®

®

®

76


A

Ad8ptet ion 0 non

tneioenee: .2· Maen : 0,6

)IE

a a

)IE '. --....

/0""

------~ , ..... -......... ----........................ ... +--..,. ....... 4 ........ _ .. __ _

-===------..................... . ... -....... .:. ........ '*""--:-'~-- .... _--

.. ...

• • A0167

)IE

A0122

)IE

! ------ AO~47

............. _-----_ .. - ............................. _- ---*-----~--~~-~-,-

" " ,-

-~ X (mm)

)( I

:I ..

Figure 41

®

®

®

77

o

f the four Use 0

tet10n ,A.dep

s - Kp base case

........ _- ..

• :

)(

• :

"'.$ .... ~~ I

I 0 .. : ;>

X (mm)

Figure 42

®

.®

@ • •

@

®

CD

78

..


,Adl!lptet ion .non

incidence: Q. +-.--....:...:--*)I(@

0,8

......... -._--........ '. ' .

:

---.~.,. ••••• AD108

'. "

.................... , -..

.........

'"

. ..

AD153

)I(

• e

AD165

)(

• : .. ----- .... ~

-..• .••••••••• ••••••••• • •••• ~ •• ~......... c. ADIOS

)(

• :

.... -.--~ .......... . .....•...... ~ ....... ~ AD153

: . -~ X (mm)

)( I

!

®

®

Figure 43

79

.l

f the four Use 0

Adept2lt1on

o· incidence:

: 0,8

:

__ non __ ._ LD

_ .. LD

s - Kp base case

-~ X (mm)

)IE

)(1

: ..

:

Figure 44

®

@)

®

80

Figure 45

Use of the four base cases - Cz Cz recapitulative

Local lift coefficients

r-----------~----------------,----------------T----------------~ I I NON ADA PTE I AOA?TE 2-D I ADAPTE 3-D I

~-----------+----------------+-----------.-----+----------------~ I I R 1 0.3600 I R 1 0.3405 I R 1 0.3027 ! I I R 2 0 . 3726 f R 2 0 . 3687 I R 2 0 . 3229 I I I w +2 f R 3 0 .4388 I R 3 0 .423:7 I R 3 0 .3:752 I

H - 0.6 R 4 0.4740 R 4 0.4715 R 4 0.3861 R 5 0.5091 R 5 0.4948 R 5 0.4127

I R 6 0.4348 I R 6 0.4250 I R 6 0.3658 I

~----------------+----------------+----------------~ I I Aile.: 0.448 I Aile: 0.438 I Aile: 0.371 I

~-----------+----------------+----------------+----------------~ I I R 1 0.2081 I R 1 0.1995 I R 1 0.1865 I I I R2 0.2154 I R2 0.2198 I R2 0.1984 I I I ".' 0' I R 3 0 .2711 I R 3 a .2537 I R 3 0 .2411 I I H" 0.6 I R 4 0 .2418 I R 4 0 .2419 I R 4 0 .2076 I

IRS 0.2351 IRS 0.2337 IRS 0.1984 I I R 6 a . 1993 I R 6 0 . 1926 I R 6 0 . 1647 I

~----------------+----------------+----------------~ I, I Aile: 0.231 I Aile: 0.227 I Aile: 0.200 I

~-----------+----------------+----------------+----------------~ fiR 1 0.0798 I R 1 0.0661 I R 1 0.0687 I I I R 2 0 • 0881~ I R 2 0 . 0819 I R 2 0 . 0799 I I - -2 I R 3 0 .0989 I R 3 0 . 0949 I R 3 0 . 0945 I H· 0.6 I R 4 0 . 066!5 I R 4 0 . 0632 I R 4 a . 06 07 I I R 5 0.0561 IRS 0.0440 R 5 0.0486 I I R 6 0.0232 I R 6 0.020:7 I R 6 0.0174 I I ~-------------.---+------------..... ---+----------------_l I I Aile: 0.06E; I Aile: ~.059 I Aile: 0.052 I

~-----------+----------------+----------------+-----------------1 I I R 1 0.2401) I R 1 0.2253 I R 1 0.2034 I I I R 2 .0 . 2 5 4~5 I R 2 0 . 2509 I. R 2 0 . 2128 I I I - 0 I R 3 '0.3082 I R 3 0.2842 I R 3 0.2488 I I H - O. 8 I R 4 0 . 375 ei I R 4 0 . 3341 I R 4 a . 3 026 I I IRS 0 .415 () I R 5 0 .3825 IRS 0 .2853 I I I R 6 0.4162 I R 6 0.3193 I R 6 0.2555 I

I ~----------------+----------------+----------------~ I I Aile: 0.353 I Aile: 0.315 I Aile: 0.263 I L ___________ ~ ________________ ~ ________________ ~ ________________ J

"Aile" = wing

81

Figure 46

Use of the four base cases - Cz

.~ 0 c - I I Q. N C") ....... 0

" -CII -c. E 0 - -0. 0. U c: 0 .g '" 0 -g > c: 0

0 + x

",,,,:;,,- / /j 0 ("I)

/

I I .

7 I r I 0 I I I 0 N I 0 I

I N + I 0 I

I I I

II I I II I

I II

I I tj tj I tj I

f

I I I

I I , 0 ,

t \ • N

I ,

I ., I '.

II I \ I I ., , ~! I

\ I I

I~ I

U) ,

\ \

I .. \ ~ C:> \

II ~ l :;( 0 . -:E \ ~. - ~ a" a ~ \\ c

u ~

0 $ - '\ .S

N· \<!..~ U \ . I .-< .. 0

LO ~ ("I) N - 0 ... ~ ~ ~ ~

0 0 0 0 0

Key

A •• Internal wing B .. External wing

82

0,5

0,4

0,3

0,2

0,1 A

Aile interne 0

()

A - Internal wing B - External wing

Figure 47


M

0,6 0,8 «=0· 0 • non adapte

A , adapte 2_D

0 • adapte 3_D

• •

B

I I Aile externe Y(cm) .. 10 20 30

83

5

4

3

2

1


Czxcorde (em)

-~ ...... ...JilL' .-... ... -:~.,. ":'- ....

.............. , .... . .......... --.'M-., ............ """ii ....

. -.. .. -\ ................

..-. . --.--

---" --. --'-"

FigurE~ 48

o non adapte + adapte 2_D )C adapte 3_D

'--.-.........:. a. 2°..-... A 11>-....;· - =-

Aile interne Aile ext~ie·-·-.~._. o o

A - Internal wing B - External wing C .. Cz x chord

,_ I

10 20

Y(cm) •

30

84

Figure 49


M

0,6 0,8 a.= O·

0 • non adapte

A , adapte 2_D

Czxcorde 0 • ada pte 3_D

5 (cnn)

4

3 ~~ .. -~-- ----.. ----~

-- --~ III '-. ._......... • .... ---'-0-._'" --. ....-

'''~'' . .... ..... ---......... ..... ........ " .-............., '''0- .......... '-- -...... '--' ......... ~ '-- ........ '--.-- -.... - .......... 0- -"", ................ . ---.-.... ""'-"", -. ,

' ........ ""'- .......... ' ''''''''''0---'~

2

1 A .B' I '--~

~_A_il_e_~,_)t_e_rn_e~ _____________ A_ile __ e_x_te_r.n._e ____________ ,,_I ___ ~rn) o o

A - Internal wing B - External wing C '" Cz x chord

10 20 30

85

Figure 50


A C A. 0,6 Cz aile 0,6 Zalle

.I o non adapt~ o non ada pte

0,5 + adapt; LD 0,5 + adapt~ 2.0 / • adapl~ 3_D • adapt; 3_D /

M=O,6 / 0,4 0,4 l

'I 0,3 0,3 1/

0,2 0,2 M .. 0,6 (T.N.) 0_

0,1 11 0,1 . -' M = 0,47 (T.D. 7·'.) ~. B compagn. Mars Yi117

f (:r.0 ao ° .. I I ~ ° '.., _4 _2 ° 2 4 _4 _2 ° 2 4

A •. wing B - March 1977 series

86

Fichier .- File Rangee .- Row Corde .- Chord

Listing of Cz

Annex 1

87

*****FICHIER * RANGEE : 2 * RANGEE : 5 **********






*****FICHIER * RAN GEE : 2 * RAN GEE : 5 **********

*****FICHIER * RAN GEE : 2 * RANGEE : 5

*****FICHIER * RANGEE : 2 * RANGEE : 5 ****** •• **



- 1 -

AD105 **** MACH = .702 INCIDENCE = 0.00 NON C2= 2.310E-01 CORDE*C:= 2.963E+Ol C2= 2.790E-01 CORDE*CZ= 1.978E+Ol

AD107 **** MACH = .599 INCIDENCE = 0.00 NON C2= 2.154E-01 CORDE*C:= 2.763E+01 CZ= 2.351E-Ol CORDE*C:= 1.667E+01

AD108 **** MACH = .801 INCIDENCE = 0.00 NON CZ= 2.545E-01 CORDE*C:= 3.264E+Ol CZ= 4.150E-01 CORDEle:= 2.942E+01

ADlle **** MACH C:= 6.918E-02 C2= 3.999E-02

= .697 INCIDENCE =~2.00 CORDE*C:= 9.872E+00 CORDE*C:= 2.835E+00

NON

ADl15 **** MACH = .702 INCIDENCE = 0.00 3D(I) CZ= 2.06~E-Ol CORDE*CZ= 2.645E+01 CZ= 2.215E-01 CORDE*CZ= 1.570E+01

AD116 **** MACH = .701 INCIDENCE = 0.00 3D(2) CZ= 2.050E-01 CORDE*CZ= 2.629E+Ol CZ= 2.270E-01 CORDE*CZ= 1.610E+Ol

AD11? **** MACH CZ= 1.984E-01 CZ= 1.961E-Ol

= .598 INCIDENCE = 0.00 CORDE*C:= 2.545E+01 CORDE*C:= 1.390E+01

3D(1)

AD11S **** MACH = .806 INCIDENCE = 0.00 3D(1) CZ= 2.070E-01 CORDE*C:= 2.655E+01 C2= 2.732E-01 CORDE*C:= 1.937E+01

ADl19 **** MACH CZ= 2.128E-01 CZ= 2.853E-01

= .805 INCIDENCE = 0.00 CORDE*C:= 2.729E+Ol CORDE*C:= 2.023E+01

3D(2)

AD120 **** MACH = .599 INCIDENCE = 2.00 NON C2= 3.802E-Ol CORDE*CZ= 4.876E+01 C2= 5.198E-Ol CORDE*CZ= 3.685E+Ol

AD122 **** MACH = .600 INCIDENCE = 2.00 NON C:= 3.726E-01 CORDE*C:= 4.~79E+01 CZ= 5.091E-Ol CORDE*C:= 3.609E+01

88

- 2 -

*'****FICHIER -: AD123 **** MACH = .61)6 H1CIDEHCE = 2.01J 3Dq) *' RAN GEE : 2 C2= 3.229E-~1 CORDE*CZ= 4.141E+01 * RANGEE : 5 C2= 4. 127E-01 CORDE*CZ= 2.926E+~1 ****':0:***** **HHl-F I CH I ER * RAt·IGEE : 2 * RAt-lGEE : 5 **********

***'H!FICHIER * ~:A~·IGEE : 2 '* RANGEE : S ****'*"if****

****-~FICHIER *' F:ANGEE : 2 *' RAHGEE :5 **********

*'****FICHIER *' RAN GEE : 2 * RAt-lGEE : 6

*****I=ICHIER * F:At·jGEE : 2 *' F:Ftt'IGEE : 5 *****,~****

***H·FICHIER .: *' RFtt·1GEE : 2 * RAt·jGEE : S

***,**FICHIER * F:AtK;EE : ~ *' RAt·IGEE : 5 **********

. *****FICHIER * RFtt'l(:;EE I 2 '* F~At·l(:;EE : ~ **********

*****FICHIER * F:At-lGEE : 2 '* RAt·1GEE : S **********

**~**FICHIER * RFtt'IGEE : 2 * F:Ftt'IGEE : 5 ****** .. ~***

AD124 **** MACH = .703 INCIDENCE· 2.00 NON C2= 4.071E-01 CORDE*CZ= 5.221E+01 C2= 6. 103E-01 CORDE*C2= 4.327E+01

AD125 **** MACH = .7133 INCIDENCE = 2. a~ 3D<t). C2= 3.361E-Bl CORDE*CZ= 4.310E+01 C2= 4.750E-01 CORDE*CZ= 3.368E+Ol

AD126 **** MACH = .806 It-lCIDENCE = 2.00 NON C2= 5.214E-01 CORDE*CZ= 6.687E+01 C2= 7.394E-Ol CORDE*CZ= 5.242E+Ol

AD127 **H' ~lACH = .806 HICIDENCE = 2.01) 3D(l) C2= 3.792E-01 CORDE*CZ= 4.863E+Ol CZ= 7.10SE-01 CORDE*CZ= 5.B36E+Ol

AD 123 ***'* t'lACH C2= 4.116E-131 C2= 7.5;21E-~1l

= .806 INCIDENCE = 2.00 CORDE*CZ= 5.278E+Ol CORDE*CZ= 5.333E+01

3D (2)

AD 129 **** ~lACH CZ= :3. '~n'E-IJ1 C2= 7. 4:=:5E-~11

=- . :306 I NC I !lEtKE = ;2.013 3D (:3) CORDE*CZ= 5.101E+Ol ~ORDE*C2= S.272E+01

AD130 **** MACH = .707 INCIDENCE = 1.50 2D CZ= 3.491E-01 CORDE*CZ= 4.477E+01 C2= 4.99SE~01 CORDE*CZ= 3~542E+al

AD131 **** MACH C2= 3.2!OE-01 CZ= 4.166E-01

AD 1 :34 **** t'1ACH C2= 2.509E-01 CZ= :3.8,:5\:-81

= .602 INCIDENCE = CORDE*CZ= 4.117E+01 CORDE*CZ= 2.954E+01

= .809 INCIDENCE = 0.00 CORDE*CZ= 3.217E+01 CORDE*CZ= 2.712E+Ol

2D

AD135 **** MACH = .702 INCIDENCE ~ a.0a 2D CZ= 2.384E-Ol CORDE*CZ= 3.05SE+01 CZ= 2.7S8E-01 CORDE*CZ= 1.9S6E+01

89

*****FICHIER ~ RAN GEE : 2 * RANGEE : 5 111*******

_***IFICHIER ; RAN GEE : 2 I RANGEE : 5 111*******

I*I**FICHIER • RAN GEE : 2 * RANGEE : 5 ***.******

*****FICHIER I RANGEE : 2 I RANGEE : 5 1*1*******

I*II*FICHIER * RANGEE : 2 * RANGEE : 5 1*11******

I****FICHIER * RANGEE : 2 * RANGEE : 5

**I**FICHIER * RANGEE : 2 I RAN GEE : 5

I**I*FICHIER I RANGEE : 2 I RANGEE : 5 11*11*****

*I*I*FICHIER * RANGEE : 2 * RANGEE : 5 *11***1***

III**FICHIER * RAHGEE : 2 * RANGEE : 5 *1********

IIII*FICHIER * RANGEE : 1

.. I RANGEE : 4 111******1

- 3 -

AD136 1*** MACH = .597 INCIDENCE = 0.00 2D C2= 2.198E-01 CORDE*CZ~ 2.819E+01 CZ= 2.337E-01 CORDE*CZ~ 1.657E+01

AD137 **** MACH = .598 INCIDENCE = e.00 NON CZ= 2.26GE-01 CORDE*C2= 2.898E+01 CZ= 2.451E-01 CORDE*CZ= 1.738E+01

AD138 **** MACH = .599 INCIDENCE = 0.00 3D(1) C2= 2.004E-01 CORDEICZ= 2.570E+01 CZ= 1.968E-01 CORDEICZ= 1.39~E+01

AD139 **** MACH = .804 INCIDENCE = 0.·00 NON C2= 2.686E-01 CORDEICZ= 3.445E+01 CZ= 4.513E-01 CORDEICZ= 3. 199E+01

AD140 +~** MACH = .804 INCIDENCE = 0.00 3D(I) CZ= 2.067E-01 CORDE*CZ= 2.651E+01 C2= 2.645E-01 CORDE*CZ= 1.876E+01

AD14i **** MACH = .804 INCIDENCE = 0.00 3D(2) CZ= 2.222E-01 CORDEICZ= 2.850E+01 r~-w~- 2.991E-01 CORDElez= 2. 120E+01

AD142 11** MACH = .598 INCIDENCE =-2.00 NON CZ= 8.875E-02 CORDEICZ= 1.138E+01 CZ= 5.611E-02 CORDE*CZ= 3.979E+00

AD143 *111 MACH CZ= 7.990E-02 C2= 4.859E-~2

AD144 *1** MACH CZ= 8.189E-02 CZ= 4.395E-02

= .598 INCIDENCE =-2.00 CORDE*CZ= 1.025E+e1 CORDE*CZ= 3.445E+00

= .596 INCIDENCE =-2.00 CORDE*CZ= 1.050E+01 CORDEICZ= 3.116E+OO

3D(I)

2D

AD145 **** MACH = .596 INCIDENCE = 2.00 2D C2= 3.687E-01 CORDE*CZ= 4.729E+01 CZ= 4.94SE-01 CORDE*CZ= 3.S0SE+01

AD146 *1** MACH C2= 3.405E-01 C2= 4.715E-01

= .594 INCIDENCE = 2.00 CORDE*C2= 4.872E+01 CORDE*C2= 4.344E+01

2D

90

*****FICHIER * F:Rt·IGEE : 1 * f~RtIGEE : 4 *i'HHH'*****

iH':HHF I CH I ER * I~RHGEE : 1 * I~RHGEE : 4 **.~*******

*****FICHIER * RRNGEE : 1 * RAHGEE : 4 **********

iHi'HHFICHIER *' I;~ANGEE : 1 * ·I':A~II~EE : 4 ********1;*

*****FICHIER * F.:At·IGEE : 1 * RAHGEE : 4

*****FICHIER * F.:ANGEE : 1 * RRt·IGEE : 4

*~;**,*'F I CH I ER *' F.:At·IGEE : 1 * RAt·IGEE : 4' *********'*

- 4 -

AD147 **** MACH = .593 INCIDENCE = 2.00 NON CZ= 3.600E-01 CORDE*CZ= 5.151E+Ol CZ= 4.740E-01 CORDE*CZ= 4.367E+el

AD148 **** t1i,CH = .594 HICIDEt'ICE = 2.013 3Dq. CZ= 3.027E-Ol CORDE*CZ= 4.332E+Ol . , CZ= 3.S61E-01 CORDE*CZ= 3.557E+01

AD149 **** MACH = .594 INCIDENCE = 0.00 2D CZ= 1.995E-01 CORDE*CZ= 2.855E+Ol CZ= 2.419E-01 CORDE*CZ= 2.228E+01

AD150 **'** MACH = .595 INCIDENCE = O.O~ NON CZ= 2.081E-01 CORDE*CZ= 2.978E+01 CZ= 2.418E-01 CORDE*CZ= 2.228E+01

R!1151 **** t'1ACH = .5'34 HICIDEtKE = ~).00 3D(1) C3= 1.865E-al CORDE*CZ= 2.669E+Ol CZ= 2.076E-Ol CORDE*CZ= 1.913E+01

AD 152 **** ~lACH CZ= 2. 25::;:E:-\) 1 CZ= :3. ::::41E-Ol

= .802 INCIDENCE = 0.1313 CORDE*CZ= 3.225E+01 CORDE*CZ= 3.078E+01

2D

AD153 **** MACH = .803 INCIDENCE = 0.00 NON CZ= 2. 400E~-OI I~JRDE*CZ= 3.434E+01 CZ= 3.755E-01· CORDE*CZ= 3.460E+01

*i~'***F I eH I ER.: AD 154 **** ~1ACH = .803 INCIDENCE = 0.00 CORDE*CZ= 2.911E+Ol CORDE*CZ= 2.788E+Ol

:3DO) * RANGEE : 1 CZ= 2.034E-01 * RANGEE : 4 CZ= 3.026E-01 ;;'''I~********

*****FICHIER * RAHGEE : 1 * RAHGEE: : 4 i·HH*****·**

*·H*,*FICHIER '* RANGEE : 1 * F:ANGEE : 4 *******~,,**

*****FICHIER * F:ANGEE : 1 * F:At·IGEE : 4 ******fHH*

AD155 **** MACH = .595 INCIDENCE =-2.00 2D CZ= 6.814E-02 CORDE*CZ= 9.751E+oa CZ= 6.321E-02 CORDE*CZ= 5.824E+OO

AD156 **** MACH = .596 INCIDENCE =-2.00 NON CZ= 7.989E-92 CORDE*CZ= 1.142E+Ol C2= 6.654E-02 CORDE*CZ= 6.l31E+oa

AD157 **'** MACH = .596 INCIDENCE --2.00 3D(1) C2= 6.874E-02 CORDE*CZ= 9.836E+e0 C2= 6. (166E··02 CORDE*CZ= 5. 5809E+00

91

;~****F I CH I ER ,~ F:A~IGE:E : 3 ,~ F:At·IGEE : 6 ,r.*********

*****FICHIER *' F:AHGEE : 3 *' F:At·IGEE : 6

*****FICHIER * F:At-lGEE : 3 *' RAt·IGEE : 6 *****~.****

*****F:rCHIER * F:At-lGEE : 3 :0,. RAHGEE : 6 **********

*****FICHIER *' F:At·IGEE : 3 * RAHGEE : 6

*****FICHIEF: *' RAt·IGEE : 3 ;0; RAt·IGEE : 6

*****FICHIER * F:At'IGEE : 3 * RAt·IGEE : 6

*****FICHIER * F:At·l(~EE : 3 * F:At·IGEE : 6

*****FICHIER * F:At'II~EE : 3 * F:A~H~EE : 6

*****FICHIER * F:ANCEE :. 3 * F:At-lCEE : 6

*****F' I CH I ER * RAtlGEE : 3 * F:AHGEE : 6

*****FICHIER * F:At·IGEE : 3 * F:AHGEE : 6

- 5 -

AD 15:3 **** t'lACH CZ= 9.48ISE-02 CZ= 2.CI7IE-'~12

AIl IS', ****' t'lACH (;Z= '? 8'?3E -£12 CZ= 2. 32:3E-'32

AD 16121 **** ~lACH CZ= ';'.454E-.n CZ= 1.742E-'Z12

= .595 INCIDENCE =-2.00 CORDE*CZ= 1.030E+01 CORDE*CZ= 1.070E+00

= .596 INCIDENCE =-2.00 CORDE*CZ= 1.074E+el CORDE*CZ= 1.200E+00

= .596 IHCIDENCE =-2.0121 CORDE*CZ= 1.026E+01 CORDE*CZ= 8.998E-el

2D

t·IOt·1

AD161 **** MACH = .S97 It-lCIDENCE = 0.0121 2D CZ= 2.537E-01 CORDE*CZ= 2.754E+01 CZ= 1.926E-01 CORDE*CZ= 9.945E+00

AD 162 **** t'lACH CZ= 2.711E-Ol CZ= 1. 9 '?::;: !;:-o 1

AD 16:3 **** t'lACH CZ= 2.4111::-01 CZ= 1.6471::-01

AD 164 **** r'lACH CZ= 2. :::4:2E-Ol CZ= ::;:.19::;:E-'jl

AD 165 **** ~lACH CZ= :3. 0::::2E-(11 C:Z= 4. 1 i.~2E-01

= .598 IHCIDEHCE = 0.00 CORDE*CZ= 2.943E+01 CORDE*CZ= 1.029E+el

= .598 INCIDENCE = 121.00 CORDE*CZ= 2.617E+01 CORDE*CZ= 8.506E+0e

= .807 INCIDENCE = 0.00 CORDE*CZ= 3.085E+Ol CORDE*CZ= 1.649E+01

= .805 INCIDENCE = 0.00 CORDE*CZ= 3.346E+01 CORDE*CZ= 2.150E+01

t·ION

:3D 0:: 1 )

AD166 **** MACH = .804 INCIDENCE = 0.08 3D(1) CZ= 2.488E-81 CORDE*CZ= 2.701E+01 CZ= 2.55SE-81 CORDE*CZ= 1.3:20E+01

AI1167 **** t'lACH = C',~,~ •• .J • • ' I He I DEt·leE = 2 •• j.) t·l0 t·l

r· ... -... .::.- 4. ::;:::::::E-(\l CORDE*CZ= 4. 76:3E+O 1 CZ= 4. ::::4:3E-'J 1 CORDE*CZ= 2.246E+Ol

AD 16:3 **?* t'lACH = .5':"':" I t·le I DEt·leE = 2.00 :3D ( 1 ) C:2= 3. 752E-'31 CORDE*CZ= 4.074E+~)1 CZ= 3.65SE-131 COF:DE*CZ= 1. :3:39E+01

AD 16'3 **** MACH = .599 I t·~c I IIEHCE =a 2.00 2I1 CZ= 4.237E-I)1 CORDE*CZ= 4.600E+e1 C2= 4.250E-I)1 CORDE*CZ= 2. 195E+01

92

Annex 2

Listing of Adaptable Wall Shapes

93

- 1 -

Listing of adaptable wall shapes (rows 2-S)

:---------------------------------------------! AItAPT.: FOF.:t'1E t'1ACH: I t·K I ItEt·KE ! ! ItEPART: 0,6 : 0,8 : ! !---------------------------------------------I ! NON :.' AIt445' : 122 : ! ! 2-D : 145 : +2!

3-D AIt'3122 : 123:: ! !-------:-------------:-----:-----:-----------1

N (I t-I : A It 4 A D4 : 1 (1;-' : 1 ° ::: : 2-D : 136 : 134 : ° 3-D :8D~10;-' AD9118: 117 : 119 : 1

!-------:-------------:-----:-----:-----------I ~~Ot·~ : AIt4 : 142 : 2-D : 144 : -2 :~:-D AD'~ 142 : 14:::: :: 1

,---------------------------------------------,

Forme depart = Beginning shape

94

F' ile: AD136 Lines of current (mm)

, N' 1-·· ..

I 2 3 4 ~

• , • ~

10 'II ,\2

Il I

'15 1\6

" II

I' 20 I Zl

22 23

I:: .. I ::5

" 2ti I I 2' I I 2& I

AbsC. tZ L 1:.H.utl~ L.r':.B •• I .... --_ ... __ I .... __ ...... __ .. 1 ............. - - .... I

-8UO 1 "'. uu U. I)u -'~4 , . U; II" .. 711.41 .101 0., -';?I). IJ • 'l~ . lot -630 4 .!i) .1":l .. S~2.1) H .4'3 .. ".;., ... ~ .~8 ... 5:2,') .~ .... 12 .. 48!?1. 'J ,.7 35 -~57.'; ."8 . J9 .. 42' , .'SIu ~u

-3!f'.:" LUof <II .... -371. 2 1. U . '411, -345.0 1 ,,~ ... ~ ... 119.f 1.... .~1 .",., 1.'~ ,'!)l .. 273.U 1. ~~ ~.2

.. 2S1. 1 .,of .,~ -~10.3· 1.''1 oS" .. 21111 l.Ll .~ .. -1"1.2 ,~o; .'l' -1:"".4 ,oIl'J •• U -lS',J ~2 .';2 .. 1"'.1i .'3 . ., j -in.s ,='2 ... 2 -12u.9 ~1 iii .. lu'l. .U .;U ... , ... '11) . j, . .,.,

I 29 -oJlJ. e~ 1)5 .~:i 30 "'~.I)~ lJ .'5.1 11 ... 'i!l 0:0 .::0 . .,11 32 "''i0.39 ." .'J?

I 13 .. 51. 3~ 3.;ot ,.; I 34 I -42.57 l . H ." I 35 I -33~!I 0103 . '55 I 36 -2'5.33 47 ')'

3" -16 94 "9 .~"'I 39 I .. >3·U . 5, ~ , 39 I VIJ . ~l ':.l

I 'ttl <U 51 . ':Ii 0111 16,j" 3. ')1 ~4 .. 2 2':0. J) J ~, ':".;

I 413 33 . a, 3. '.I . ~..: I 4.. 42.'57 1 ~\J .::.,;

4' , 1 39 J . "'i~ . '5 j 46' 61) . l~ 3 .,,~ ~.j

4' 69."iU J.~~ ~~ , 413 7'.09 3. -u S-. I ~9 o)B.~9 J JB .:4

I '0' " . Oil 1 H . ':' 1 ,~l. 109"?] 327 .~l

'2120.941 3.11J . .,.;0 '3 132.P3 .09 .~2 54 1"','56 .57 .~l ~'I 159. 13 . H 6''1 56 1'" .. 3 :'~ .• 1~ " 1'31.:3 .'57 .-,7 58 I 210.Jl .57 .1f1!o

5 !II 210 Z' ... , .4'5 '0 ;l'H.l' 2.31 .. .. 61 I '2"71 .• " 2 • 15 ... .. ';2 I 29'. ,.. 1.'9 ."" '3 I 31'.90 1.134 ~3 6.. ' ..... 98 1,'1) 43 ," 3'1. 23 1.5, . -,3 6' "S .'0 1 .041) , "1 67 "27. '" 1 .25 . )111 'I "'5'.~5 1.11 .J' U II1II1' . .." ,99 33 ~O I 5'22.01 ·8' JO

--,---- ----,---

Haut = high Bas = low

2

File: AD134 Lines of current (mm)

: ~ ~ ~ ~ ~ ~~ ~ ~~:~ ~ ~~ ~ ~ ~~ ~ ~ ~ ~~~ ~ ~ ~~ ~:~ :~~::: 1 -800.1 0 'JU IJ 'J" 1 .. ~ ... " ,Ub

j ""11." . j.J I" .... ,0.\1 .JO

0; .... JU."I . ""Ii i ,,5:;2.. .J~

., .. I)~'.I) ... :a 8 -~12.a .S< ., -,,"9.1J .• J

1'" .. ,"~._ .7 .. II -~27.~ .0"$ 12 ." .. ~., .w,

I 1l .. )'1.2 l.U I 1~ -J"'.U '.2~ I 15 t -U'.9 1.,,)

16 "295.j 1 'I' 1.' .. 2'3.0 1 .~, 18 .. ?1.: ·l.11 u .::30.3 l.u" 2. -2Ia.l 2.2' 21 ."1.2 2.II1II2 ~:! -174... 1.b'l 23 -nt'.l 2.~ .:'4 -145.6 2.1:II'J 25 -132.' lOu 26 ... lfiO.~ '.0' ~., -'u~., 1.18 4!9 .... ~~.I)tl 3.'2' '29 -lIie.tI~ .i.3~ lu .... ;O~.u:t J . .qi Jl -"9.~u J.,9 l2 -",1J.39 J.lti 33 -51.H' 3.:"9

'34 -42. " J." I 35 ... 33.39 J.'2

:iti -:5.JJ 31 .:t~ J? -lO;.~.q 4.u2

, H .. 8.011 ....... 5 I)~ OlllJ ~.o,

I 411 !oJ "'1 4."" 041 1';. Jt.. ".09

•• 1 •• 1 .~ 1

I 46 • ., , ••

1"'':1 1 50 , 'I I 5: , '3 I ~ ... , '!I'i I 'ji)

,. 59 ~" , I

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I '0 I

~!I . .JJ J3. 'J~ "2.51 51 J9 'iu H oi~ ';)tJ ":"9 Il~

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:,~19. ":"S ~~'J ':'~

1Z~. n lot'S !Iii 1'::'] ';3 17..:t "IJ 1~1 .21 210. Jl ~JO .".., 'Z51 1? '2"',) 05 2~5 ~4 319 ~o '''40 ~e 3"'1. :3 l".l~. "0 ",2;1 "6 "5~" ~,

4089.05 522 U1

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95

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File: AD144 Lines of current (mm)

..... ........... ................... __ ............... -.................. -......... N , a:lbac. ,~ L.C.Mau'\l2, to ,'; .e •• ,

: ........ 1 ..................... 1 ............... __ .. 1_-_ ................. ,

1 , .. ~OO .1 2 , ... ?54.7 , , , .. ..,11.~

I ~ , ... "0. III I ~ , -no.~ I , I ","2.It ,

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:l , -427.~ :2 .. ,~ •. 7 ,3 .. )71..,

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, -lit.'

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I ;. I -2".2 I .f -;1').1

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11 -51. I, I. .. 42.S,

" -33. a, II -:5.13

0 17 -61i .~ .. -e .. l! 0 0'0 ., ; .. . ; I< ... .: .:~ 11

I .. 3 11 .~' I .. ,2 5'

.. ! 5; ,. I •• '" 19

" H '0 .. '9 " I ., •• ~ . 0 .. , 99 · ,,4 , .. I 109. ~"J , " I 1:0

_. I ~3 u~.e3 , ,. loll, .5' I cc ,

'" 3J !6 174.43 57 "\ · ~3 I H , 213 .Jl

" 230 l~ ,~ 2" .17

I Ii ~ I 2~1 · ., I .2 I 2" .. I ~3 31'. !O I .. 1""'.'8 I .! 171.21 I .. , 39'1."0 I ", "'2? .4to I n 45'.55

U 4".05 '0 '22.01 , __ ,

Haut = high Bas = low

, U. vI) , U. ut.l , .IJ~ ". uu · .~ · .1 · ., .01

11 .~1 I I~ · .1

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" •• ,~ -. <;Ij -, 0 .55

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\. I> .• J'j 1 .1l-.1 ' .,.~

.·rJ. .j; · b~ .17

I .,. .20 ,. .6' .23

---- ----

3

File: ADl45 Lines of current (mm)

.......... -... _ ........... -- ... -..................... -.................. _ .. I N , Abac. 1% L.C.KautIZ L ,'::'. ill •• I 1-....... -_ .... -- ........ 1- .. ----.. • .... 1 .... --- .... _ ..... I

1 -'00 .1 , 0.00 u. uu 2 -~~., , .1'41 · , . , ""11 ... .~, ~'1

~ ... "0.0 .3. · .~ , ·.JO .• I .51 . .. ..: I , -5'12.oi .. , .>0 . -~56. 5 . .. ,',

.. '22 • .~, · ~. J

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I " -2,,5.! 2.4Z 1.11$ I 17 ... :'73 . .., 2.U 1.041) I :t -1' I. 2 2."1) I ,. I .. -21~. j 2 .•• 1 ....

2. I ":llO. J ) .1'7 1 .. :1 .. 1'11.2 l.h I " 2Z -1'''.04 l.S' L.,1

0 :1 "1!' .3 '.'S I e~ H "14~ .Ii l.*,'f 1 ' • .!

" .. 1.32.11 ".tl1 I .~ J

I ~'i "l~O ., 04.11 I .,. 0 2' -109 ? ~.21 I ... I ,e .. !o~ ~, 04. '2 I .5 ,. -.9 .s. ~."l I . .0

10 -~ .1.1' ~.'I I . .. II "09 •• 4.S0 J "I

I j:! .. 0;') · S? ~.'i • u> I 11 -51 3~ ~." 2 . ". I. .. 42 5 • ~.U · u~

I, , -13 ~. ~.~8 r.':

H I .. .!'~ .33 ~.'l IJ::"

" -tli .. ... " '.'? ~'1 -s . .0 4.'tt u. H- 0'.00 S.IJU , . 'J~ •• I Sf·""1 , ... J 0'; .. 16 .3<4 , .IJO 0: . 'i~ .2 ~';o. 'j1 , . It.., ", ., 13. ~i ,. vI)

~ , .. 57 ,. U!J , "': ., I . ~ t ,1 ... t~ 1 '.' .. ... , O;:O.JSo 4.t? 'l'J ., , " .eu 4.'1-4

49 , ".. · u~ 4. ~u

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53 112 H ... 41 ,. ,~ 1-1'5 .'So IIt.2:=' " I " , 1'!1 31 4I.U .:''l 5. l'4.·U 1 3 .~'!l' 1."\:1 ~7 13l.23 ,. is I

I '9 I :\0.3\ J. 'u I • ~'!" ~. 230.2:' '.53 I .5J ,. ~'H.1' , J .lot I .4'!l' , H , 273. ~, 1.11 \ .-1" , '2 I 2'5 .~ ... 2.91 \ · , . • 3 31'.90 :2 .69 I ,. .. J~4.!" 2 ... , I · .~"",

I ., 1'1.'1 2.24 l.U I ., lh .,,, 2 .• 2 1.1'1 ., "17."4' 1.~1 1. uo;

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'--!-- ----! -----,-----_. ---!

96

- 4 -

1

Flc'"ller ; A0142 Cotes des parols (mm)

-------------------------- ----------~l 1 Ab~c. IZ F'1.K41.lt. Z Pl. B45 1

1---·· 1---------- ---------- ----------1 1 1 -705.1) .24 -.34 1 1 2 -575.0 .66 -.72 1 3 -460.'3 1.13 -1.00

4 -355.0 1.45 -1.42 5 -275.0 1. 69 -1.70 6 -215.0 1. 76 -1.87 "7 -155,1) 1,99 -2.ll 8 -95.02 2.24 -2,13 9 -35,02 2.41 -2,40

10 :4. 9~ 2.46 -2,64 11 , 84 SI~ 2.59 -2.69 12 144.93 '2.9:2 -2.83 13 204.'33 3.0' -3.05 14 284. :0:3 3.1':1 -3.23 15 3'39 . ~'3 3.43 -3."2 16 1 S!}4 38 .3 7'; -3.8~ , ,

------._--- . -------- --------Fl.:hur : AD144

N 1 Ab~,:·. 12?-1 ;-(~'.l": 12 ?1.3o!l5 .I 1----1----------1----------1----------

1 1 -70~;.~ .37 -.21 :2 -5?~) 0 . '~/ - .70 3 -460 ,) - .33 -1 II 4 -35:; tj 2 !lSI -1 ,"1.8

5 1 - 2 ~l~) !; '2 .55 -1 ,94 6 -215 ,) 3 Jjt; -~ .28 7 1 -lS:) !) 3 4'; -2 '52 e -':5 0: 3 92 -., . :;'7 -9 -::5 ~J :1 4.'51 -3 ')6

11) 24. '~:~ '1.78 -3 .:2~ 11 ! 84. ':8 4.91 -3 ,35 12 1 l'l4 . ':06 4 91 -3 ' '18 13 204. ,?:~ 4:32 -3 .'\9 1'1 2':4:. :38 4. 7:~ -3 ,::.s 1S 389 . ~:3 4. S'* -3 ,5:i' lS 5iJ".~?:3 to! ,"' -:: 78

I I ~ I • . ---'- . ---_ ..... _---- . -------- . -----_._-- .

Fichier = File Cotes des parois =

Wall specifications Haut = High Bas = Low

Non adctpte

:l.ChH!:' : 'AD143 Cote~ ~e5 ;~rO~$ (mm'

-------------------------------------

7 1 :3 ! ':I !

"' :":

~ 1 12 13 14 !

1'5 16

-275 C -215 'J -155 oJ -':IS ,1}2 -35 c::

2-! "~O:"

3 .. 1. ~6 14-',98 ~O4.98 284 . :<'~ 3:39 .'I~ .• = '30496

2. 32 :.2 82 3 23 3 Ii> 7 '''';'s I

,';2- - 3 . ~3 ,I , 4 12 -.:i '17 4. '!t:i -.3.53 4. OS -3.~4 3 ,7~ -3.68 3 . '1:3 -3 >38 ,~ .137 -.3 . :':.2 2.34 -3,87

, I • - -_ .. - ...... - ------- -----_. ---_._- .

97

5

Flch,er : fol010" Cot •• d •• paro u ("''''')

H I Abac. 1% Pl.Haut 1% Pl.a •• ---- 1----------1----------1--........ -----1 1 I -705.0 .24 - .26 2 I -575.0 .63 -.66 3 I -~60.0 1.05 - .99 4 -3".0 1.45 -1.45 5 -275.0 1.69 -1.73 6 I -215.0 1.U -1. 89 '7 -155.0 1.99 -1. 9'4 9 -" 02 2.23 -2.13 , I -3' 02 2. <13 -2.41

1~ I H 9~ 2.50 -2 . .q6 11 I 94 99 2.79 -2. So 1~ I 1~4 9d 2 93 -2.90 11 204 99 3. J~ -3. 11 14 2-34 93 3 21 -3 . 2~ :~ 3~'~ ;9 53 -3.55 l~ 5·:4 ~'3 3. ,.:, -3 9l . , --------_. --------_. ------

__________ 1_-.... __ ----- 1 ___ ......... ____

-~:5 0 I .:3 I ... '11 -!':>'j . ~ I B -.51 .. ·H·) J 92 - 72 -3~~ .0 .71 -1 . u,i -'2":"5 .0 lu -I .12 .,:! ;p) - 1 2'; -::~ "i3: 00 -:! '- ! ~ "'i -!~ .. , 5 " .. ~";.j; .. U~ "'i ~4,9d 6 ':'2 -2 .,

'- 144 H 5 S;IJ -2 ~:;

:l ~')-t .. 5 -i .. -:: .0 -~ 2-;4 ~: .'l:! -2 ~~ . : 339 :H :g -3 . 2~. ~ : 5 1:"i 3'3 't. e~ -3 ~o

-------:' ------! -------f''="l,r ~('I!!7

~c:~., C!~S o;U'C 1S I""",)

1 ___ - • ______ ....... _1 ... ____ .. ____ 1 ____ .... ____ I

I

Fichier .-. File Cotes des parois =

Wall specifications Haut = High Bas = Low

3 ~

5 6 ?

10 :1 12 I~

1-1 :5 16

_7'.':. 0 -5"~ 0 .. ~£ .: 'J -3~ , 0 .. 2:-~ J -2.5 0 -1,!5 .0 -ii'S .Il::! -35 ~2 2~ .93 3~.~9

lH.fl ~04. '9 2H . ~ 3 3f~ . ~1 5(4 ~a

-----

... ~ I - 2S

.12 .. -. 'Ii 1. ~6 -I 00 1 3'i -I. 25

31 -I 51i 2 e" -2 0::-3 . :13 -2 :ti 3. 51 .. 2. ,-:: 3 ~9 -3 H 3 ;0<1 -3 .;00 3 45 -~ 14 3.03 -4 .63 :. ~? -5. !l I. ~5 -5 .~o

. ~6 -6 .4? - .5d ... :"" H

Non adapte

2-D

3-D

98

6

henlOr , AD122

1 H 1 Aboc. 1% PI.H ... ~ 1% '1 .••• 1 ----1--------··- 1 __________ 1 __________ 1

1 1 -705 . 0 1 I." 1 ." 1 2 1 -57'J. 0 1 J . 15 1 1.10 I 3 -"'0.0 1 4.55 1 2.30 1 'I -'55.' I s.n I 2.U 1 5 -27'J. 0 1 , .70 I ,. 'I' 6 -215.0 I 7. 4Z I 3.7' ., -155.0 I 8.05 4.11 8 -95.02 I 8.70 4.33 9 -35.02 j. 52 4.93

10 24.98 10.22 5.0J II 84.59 10.96 5.44 12 14'1.9i 11.58 5.~7 13 204.99 ! 2.29 6. !l 14 2t4.!$ \3.'25 ~.6' 15 !It.fa !4 .• 7 7.21 !6 594 ... 9 1'.';, 7 ;: , , , -----._---_._---_.

F:.ch:..!, ~t.'14~ Cot •• ~.s ;'&:C:'l (~m)

" I Absc . IZ Pl !-: .. <.;t I~ Pl.2&. 1 ......... _! ---- ..... _~. __ 1 ... - -_ ..... - ......... 1 .. _ ... _ .. _____ I

-':"~! .'J . .s .. )" .. !?15 .0 ~,) .... 'J,;

l I ~4'0 0 l. .... :;:lo 'I -1" Q :i - .2; ,5 , -z" !I 4. 19 -. :~ • -Zl'! 0 4 -:~ .23

-l~5 .0 ~~ 2" -95 . O·~ • "U " ~

~ I -35. O~ , ~O - l4

Ie I ~4.9!j ,. 4~:' -.5; I li- I IJ!4.fa 7.44 .... '; i I I: 144H ., ." -1 .';:"'t .... I ~O ... -:9 ;, .15'5

1'; 2S~.9~ 3~ -1 . .,.) I' , 3·1g.91! ~5 -~ .!oj I~ I 504.9a 3,) - '1: , ,

----------"---------- ---------Flchler : ~Ol~3

Cot •• d •• ~.:'~~I '""m)

, ~ I ,:os::. I: Pl.!'(sl.:.t IZ?l : ... I 1----: --- .. ------,- .. ________ 1 ____ ........ ___ I

""\l~. 0 1. ,e ~~ 2 -5;~ .0 3.13 I .62 1 ,

-~~ Q. 0 ~ .5~ 2 3~ .. , -S-S5. a ~. 02 l ~;t , -27~ 9 '.12 1. '::3 6 -215 .• • .03 ) J~ , -15'.9 I.U 3.50 • -'5.02 t.7" l.5Q , -35.02 10.16 3. ~o

10 2 ... f8 10.41 :2 .~~ 11 .... ,. 10.10 '2 .~, ., 1:! 1~4. '9 of .9l 2 4. 13 , 204. ~8 3.H , ~ . ~:-H , 2'<1. ~8 :3 . .;~ ., 1. ~: 15 389. i'~ 7.50 I 1. u~

I 1~ , 51)4.')& , .55 I . '5 " , . --'---~--.. '- !_-----,

F'ichier = File Cotes des parois =

Wall specifications Haut = High Bas = I~ow

Non adapte'

2-D

3 -0

99

Fichier .- File

7

hel".r : ADlaS Cate" 4 •• parol. (ftIfII)

I N lAb... IZ Pl.Haut IZ Pl. ... 1----1------____ 1 __________ ----------1 1 -'05 . ° I .21 - .2' I 2 -57$.0 1 .n -.U I 3 -450.0 I 1.04 -.It

4 .,,, .• I 1.46 .1.45 5 -27$.0 1 1.5' -1.'" • -215.0 I 1.S9 -1.88 , -1$5.' 1 1.9' -1.94 • -n. 02 1 2. 2Z -2. 13 , -35.02 I 2.43 -2.4a

10 2".98 1 2 50 -2.46 11 84.~8 I 2.79 -2.P 12 144.9'1 1 2.aZ -2.89 13 204.9a 3.aa -3 11 14 2~".99 l.B -3.2' 15 399.~'l 351 -;.~5 16 504.H 40') -3 .• ! ! __ 1 _____ ! ... ________ , ____ ,

"1.l!:h:'.fr .:ot' .. .!"t CO~4l. :tes ?.\r:l:" 'la1ft,

N I Ab.~. I;':?l !ot."u-:. I: Pi =a, 1- ........ 1-----... - ................................ ! .................. _ .... I I l' .. '05. I) 4"': .... :~

I I

I I

2 I -'7!.(I ;:! _.~~

l -460 0 33 -.'7 4 -355.0 .~2 .. 1 !l9 ~ I -275 .. ) .• 5 -1 .• 0 ~ -215.0 4 0: -: H '7 -153.') ~ ~3 -:J $ -9~ 02 ~ .. H ,

la 11 l~ 13 I

14 15 I

1~

N I

... 1' .~:: 2'\. ie !4 93

1-l4.-:'1 20<4. ~3 294 9~ 3n.~9

'0 ... 9>3

!3 .44 .5" ., . 01 74 55 47

-2 -2 -2 -3 -! -3

.9 ~3

~8 .oii H ~3 40 .il ______ I _~ _______ ! ____ _

ItlC:~U!" ':'0119 Cot ... c~s ,._:-0:'. ,""',

Abs':. '2 P1 M .. ·.lt 12 Pl.S .. u I ... ---, .... _----_ .. - 1---..................... .:._-------- I

1 -,a5 a .4oj -.51 2 -575 .• J .57 ... . e~ ] -~~o a 1.4~ -1 39 4 -3~5 • Q "2. O~ -! ,,~ , -~75 . ~ 2.53 .~. 33 , -215 0 ].01 -2 .• ~ , -1". a 3 .14 -J .36 8 -".02 4.11 -l.ts 9 -35.02 ".'1 -4.52

1~ 24.99 ".U -".H 11 84.93 4.2'. -,.U 12 144. ge , .. , -, .~o !3 204.'19 3 .• ). -li.11 H 2~4. 93 2.3' .. ';,71

l' sa9. ~e 1,21i -1 .0 is ,.~. 99 .45 .9 .b~ , ---'------

Cotes des parois = Wall specifications

Haut = High Bas = Low

I M= 0.8 I 0(= 0 0

Non odepte

2-D

3-D

100

Annex 3

Listing of Test Files

101

Key to Annex 3

Fichier ::: File Parois rectilingues = Rectilinear walls Symetriques = Symmetrical

Page format:

MACH HIGH AND LOW WALLS MACH LATERAL WALLS AS07 WING

I HIGH LOW I HIGH I~OW I MACH I MACH I MACH

DBL. RECORDERS UPSTM PTHOLE

LFT. LAT. RECORDERS

DNSTRM PTHOLE RT. PTHOLE

RT. LAT. RECORDERS

LFT. P'fHOLE

NECK RECORDERS

102

1

LISTE DES ESSAIS "AILE AS07"

~**~.~~~~~~*~*~~~~*~~~~~;;~*~~~~***~~*~+*.~+~~*~~~~~~~~++~~.~~~-+~~++~~~-

;; FICHIER AD4 PAROIS RECTILICNES DIVERGENTES 4 '+ ADH"5 IDEM + ROTATIIJN DE 30' 0.: ',iER:3 LE HAUT) 4 ;; AD___ : FICHIER DE L'ESSAI N 8___ .. ;; AD9 ____ : CALCUL 3-D DE LA NOUVELLE POSITION DES PAPOIS ~~+*~~~*,**~*~~~~~~~~+~~;;~~~~~~~~~++**~**~~~*~~***~~*~+~*~+~~~~*~~~+~~+~

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2'~ .~li .~12 .710 .712

r'lACH "

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.; PRr:3E:~ LAT.

• 6'?'~ .:-013 .707 .702 .7133 . 7113 • :-08 .70:3 .715 • 7'1):3 .:-07 .712

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• iQ:3 * · (~J7 * • (1)5 ;; .:-131 ;; .7'~2 * .704 • .7134 • • ~(11~ :.:-. ~~3 ~ • (1)4 • .7\)6 .; ,7'113 :.;.

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.; PRISES LAT. DROITES. .70~ .7CJ6

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.7~9

• :-1.2 .7(14 ,7Lj7 • 7~17 • :-11

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• :35'? • (1:)4 .:-10

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MACH PAROIS HAUTE ET BASSE MACH PAROIS LATER.

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? 10 11 12 13 14 15 16 17 ,I :3 1'~ 20 21 ::;:2 ', . ., '."'

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· ?;.l , ?.ll • 357 . " • : j j

: ~~ • ~'".-.J

/1 $ ---A.

·17

.~*~~ ************************ FICHIER AD127 Na(IT'~ 1 21/ 9 85 I~H2~ AS~7 M=.8 I=+2(+1.5+POT.3e') R 2-5 ADAPTE 3D l'ITE. AD127 DE AD 126 l'ITE.

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11 12 13 14 15 1'; t~ .,

'I :3 Ll

33 34 35 36

~4 '55 '5';

,57 '58

-

MACH DE REFERENCE= .8Q5~ TI'./=2'~'? '? K .

UINF= 231.108 M-S PI',/= 1~51 r'18

MACH PARors HRUTE ET BASSE * MACH PARors L~TER.

HAIJT

• :320 • :31 " • :312 • :31)5 • ,31)1 • :::~:3 · :301 • :3e~ • :31):3 • :30:3 • :305 • :3132 · :304 • :3~)4 • :305 .:3~H

• ;3a7 • :30'? • :30'3 • :30'3 • :3~7 • :308 • ;312 • :312 • :314 • :31:3 • :31'" • :?-1:3 • :3;;;5 · :313 • :326 • :32~ • :325 • :319 • :323 • :321 • :324 • :322

.82:3 • :322 .:32'3 • :31 7 • :311) · :30:3 • :306, • :313';1 • :3~):3 • :3136 • :3134 • :3~6 • :~~)6 • :3~):3 • :3137 • :313:3 • :31):3 • :31';' • :315

8A:3

.n.;

.813 1

.81313 • :313:3 .8e6 .8138 • ',3137 .807 .:312 .302 .SQ2 .SQ2 • :302 .8136 .813:3 .313:3 .:3137 • :3134 .8133 .3136 .81)5 • :3132 .79', .:31:11 .'.1133 • :3132 .79 13 • :3~)4 .8135 .3135 • 79'? • :3~4 .80:3 .7'39 • 7'~9 .79:3 • 79 toE

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• 7'~9 .n'5 • 7,,13 .7'32 "I~'~I

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• 7":~ • 79:3 • 7"1) ~~~

• (I.

HAIJT

~ PRESES DOUBLE;

• 8~) I • :313'5 • .~1J7 · :,07 • :3134 · i8':

.;..

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~ PRISES LAT. GAUCHES*

• :30~ .7"39 • :311 • :3137 .:306 • :31 13 • :3~)8 • :312 • ::,1:3 • '?'~J7 • :::04 • :30'3

• :3·)2 • :31 I) • :312 • :~~j~ • :~e2 • :3137 I ~302

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... PPI:3&:'3 LAT. DRiJrT:::~ ...

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76 ..,.,. ! ,

· :310 • :3(12 · :::06 • :::04 • :317J3

• :;:04 • ,38i • ;2.tt4 • :3013 • :304

r'lACH' r1ACH * HUB. A~10NT :3:3 • :305

4 5 .; 7' :3 "

10 11

· :304 • :313:3 • :202 • :304 • ;3e2 • :3e 1 • :313 1 • :30~J • :3~3 • :3133 • :31:1~

HUB. AIiAL

7

• :304 • :302 • :301 .;3132 • :31313 • :3130 • ,300 .:Nl • ,3130

""=1 -· ... ~ .7'N

34 .35 36 :37

• :304 • :3Q2 • :307 .:3135 • :304 • :302 • :3132 • :30:3 ... • ,3113 • :301 • :313 1 • :31:113

HUB. DROIT ..;.

4 '5 6 -,

• :306 • :3136 • :3136 • :31:1'; • :31)6 • :306 • :31i.16 • :306 • :306 • :30i • ,3136 • :306

• ::,138 I ~'3(

• :3,j 1 1;""9:3 · (',6

... HUB. GAUCHE 12 13 1 ... 15 16 17 1 :~ I'? 213 ~1

• :3136 • :31~ • :31', · :318 • :329 • :3:38 · :338 • ;3:32 • :32() 4 :326 a .3.2,', • :3 1:3 • :310 • :30'3 , ~'?'? • :306 • ;3€t3 , :;~3:3

• .34;3 • ·31'5, .? ::6 .~:31

1. 141

• 7"?:3 • :::~2 .:3134 • :313:3 .·~O~J .7','; .7',:3 .7'?4 .7',7

· :--'~', • ~'3 3 • ~:3~ • ('!3:3

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• :3~ 1 • ;",'3~j

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• :3106 · :306 • :31,)5 • :3136 • ,3137 • :3~):3 • :306 • ,311 • :314 · :31 ':; • :32'3 I :32~ .:318 • :3113 • :306 • :306

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:+ :+ ... ... ...

'5

11) 11 l' 13 1'~

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· :341 • '? I'?, • :3'~:3

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10 11 , ,~ ... 13 14 15 16 1 ;" 18 I', 213 21 .22 2:3 N 25 26 2i

18


HAIJT HAIJT f'lACH MACH ..;.

• :31', .7"'S .:3~1

~ PRISES DOUBLES ;0 HUB. Ar'10~lT • ,3g', ..;. • :318 • :311 • :3~)3 • :31313 • :3,)5 • :305 • :30', • :3139 • :311 • :3g6 • :3~J,) • :3132 • :3132 • :3-):3 • :3e:3 • :~~)4 • :3~)6 • :3135 • :3,)7 • :3g'? • :31:3 • :31 (' • :316 • :31 i • :31:3 • :~Z6 • :32:3 I ;~;3:3 "'~'~

• '.J'.'.J

• :344 '!o"';:'

• '.J'.'J

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~ 5', .3135 • :306 '"' '" 6,,) • :3Hl • :30:3 ;.; '" 61 • :3~)3 • ,3~'; ~ ~ .. '" PRISE3 LAT. ~AUCHES",

..;. 6,; ~ 6:3 ..;. 64 '" 65 '" 66 .:.:- 67' ..;. 6:3 ~ 6'? :tio 7~)

..;. 71 .,', '-7'3

• :306 • ::,01 .%18 • :30:3 · :;0', • :322 • :325 · ,3:31 • :3:31 • :314 .:H 1 • :3,)5

• :301 ;.; • :311 * • :3Hl ;;-• '30'3 ~ .81ZJg ;0

• :3135 ;.; • :3,)4 '" • :313:; * • :302 '" • :301 ;;. · :3e': · :315

..;. PRISES LAT. DROITES ...

77

• :3,)8 • :3~)5 • :3138 • :302 • :3013 • :304 • :317 • :325 • :322 • :338 • :354 • :357 • :35,3 • :351ZJ • :~~7 • :343 • :329 • :31', · :316

• :310 • :30:3 • :3g4

• ~36Q · '?42 · '~:36

1.147

• :384 • ·3~J7 .304 .300 .381 ~"4

: 7'~:3 .73:3 .7'?3 .,'34 • (',:3 • :3e2 • :3~JZ • :3g0 .7'37 ,7'37 · ,',', • :313 1 • :30:3 • :3~) 1 .3e5 • :306 • :3('2

• :3:31 :0 t .~ · .~ .... ~~ ...

• I I I

.,.

1 • :302 2 • :3131 3 • :3~ 1 4 • ,3134 5 .301 6 • '301 7 • :3a~) :3 • ,',9 " • :313 1

Ie .:3131 11 .:303

HUB. AI/AL

7

';' 1 ~t 11

:3 '?

18 11 12 13 14 IS 105

, :3e7 • :31·) • :309 • :3ao;l • :308 • :3139 • :31 e • :307 • :3Q:3

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40 41 42 4'3 44 45

• :307 '" • :3~S ~ • :3e7 ~ • ,305 ..;. • :3134 .,. ,:31J:3 ~

• :3'~H '" • :3a7 ..;. • :3l37 + • :~~3 ~ • ;31.-):2 ~ • :30e +

HUB. DROIT * • :31)6 ..;.

2 • :3136 .;. ·3 , :3~6 ~ -I • :30>,) .;. S • :3136 ., 6 • :306 .;. .. • :3,)6 .;. :~ • :307 .. '? • :3136 ;;.

IJ .:3,36 .;-11 • :3,)6 ;;. 1.2 .:3136 ;.; 13 • ',~(j6 .;. 14 • :~~)6 " 15 • :31315 '+ l~ .3136 '+ 17 • :3g7 .;. 1:3 .:3(16.;-I'? .:3136'..;. 2') . :3136 '+ ;!l .:3~e ~ ,.~ • '3e6 ..;. 2'3 • :306 ~ 24 • :~j,.)6 ~ 25 • :3~~ ~ 2-:: • :3~Jt05 +

· :3~6 ..:• ;~~6 ~ .%16 .. • :3g6 " • :3~)6 .. • :306 " • ,306 .. • :306 ;;. • :306 .;-.ag;:; .;-• :306 .;-• :~~)6 '" • :31ZJ6 .;-• :306 ;;. · ;~o~ ~ • :3~6 ~ • :;06 ..;. • :;06 ,. • .3~f'5 ~

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•

19

******_***************.***.*** FICHIE~ ~D129 N0(IT)= 1 21/ 9-85 10H50 AS07 M=.3 I=+ZC+l.S+ROT.30') R 2-5 ADAPTE 3D 3' ITE. ~D12~ DE ~D~123 l'ITE. --------------.--------------------------------------------------------_._-----

27 28

I

MACH DE REFERENCE= .80:3 TI',/=.2"". '3 K

UINF= 231. laS M/$ PI',,.'= 1~4', t18

MACH PAROIS HAUTE ET BASSE * MACH PAROIS LATER.

HAUT

• :314 • :~Ijo .:3132 • :31)5 t :303 · :305 • :306 • :30:3 • :::135 • :301 • :31)4 • :31)5 • ;3~J7 • ::aJ7 • ;3~7 • :311) .:N:3 • ::aj7 • :31):3 • ::: 1:2 • :316 • :31:3 • :314 · :315 • :325 • :32:3 • :340 • .3.35 • :345

• :344 'j"""

• '.".' I

.,H1

t :342 • :::41) • :34:3 • ·:::3:3 · :335 • :3:35 • :~26 • :317 • :315 • :313 • :316 • :317 • :31 S • :312 • :31:3 • :311 · :~ll • :312 • :31:3 • :311 • :311 • :311

.7',7

.80:3 • :30:3 • :31-)4 • :306 .81 I) .81)0 • :313:3 • :30:3 .:303 .:3% • S~j7 .805 .80:3 • '307 • :3 134 • :30:3 .3135 • :305 .307 .80S • 81)2 .7'?" • :3e:3 • ,,1)5 • :3135 · S~'2 • ,3»5 • :3 135 .3 1)5 .7'?·' • ,305 .:N:3 • :300 .7'?" • :3(h) .7":3 • :3 1)0 .n', .8131) • 801) • :3 1) 1 • ,302 • :303 .:302 • :3(l2 .:301 • :304 .:30S • :307 • :3»:3 .8 1)6 • :31)9 • :311) .:306 .8 1n .7'?6 .776

HAUT BAS - r ;;. HUB. At'10~lT

59 .803 .80~ • 60 .807 .S08 + 61 .S08 .S05 •

~

PRISE3 LAT. GAiJCHES*

• :3tJ., • r''?'' .:312 • :31J7 · :305 .n4 • :32'; • :329 • :;:32 .:~ 1 '3 • :312 • ::: 1·)

PR I :::ES LAT •

74 7'5 7~ 77'

• :;: 11 • :~04 · ,:.J~ • :::;a4 • :;'135 I '~~j7 .;,15 Q :3~24

• :319 c :336 • ;~~54 I :~~j7

• :351 • :347 • ',~~4 • '3':'5 • :~31 · :317 · :316 • :::137 • :313 • :~08 • ,308

• :3~'5 • :312 • :30'3 • :3~J6 • :3~'S • :3~j!3 • :304 • :305 .805 • :3~:1Z • :31 I) • :314

..;

DRIJITE:3'+

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PF: I :3E3 COL

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1.14';

1. 21 " • '~8'7 • :376 .a17 .777

2 :3 4-S .,; i' :3 "

113 11

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HU8. ;:WAL

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8 "

10 11

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+30 .:31':1 +31 .:314 "'32 .:312

•

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HUS. DROIT ...

2.7

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• :306 ... .:306 .. • :306 ... .806 '" .SOo ... • :306 +

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10 11 12 13 14 1'3 16 17 18 1 '? 21iJ 21

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• '?74 .?46 .,. . .,', • , ~'J

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I;) I

20

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:3 ';'

10 11 12 13 14 15 105 1-"

TIV::294.e K PEV= l~Z~ M8

MACH PAROIS HAUTE ET BASSE MACH PARors LATER.

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.~Or5

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• I _.J

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-· .... rz • f":'.,J ~., .,

,I _.,.I

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.;"24 -')-

• 1..,1

,72~ .(,24 .714 .;"21 .71 :3 .717 .715 • 716 .7'15 .712 .70:3 • ('0';' • 7~j:3 · (~J:3 • 7~j8 .707 • 7~J2 · ~',6 .0:35

.7~2

.(~7

.7(l5

.704 • 7~)5 .(~(

• 7~1S .702 .7es .700 .71)1 • 7~:3 .7~5 .70', .711 .7005 .704 .704 .70:3 · 7~J4 • 7~J:3 .702 .700 • 701 • 7~) 1 • 7~) 1 .700 • (,Cl3 .704 .704 .713,) .705 .704 .7132 .7132 .7a:3 .701 .702 .701 .7,)1 • (1)2 .702 • 7~~:3 .(~4 .703 .7134 .7c'):3 ,785 .705 .7005 .706 .704 .706 .('~(

.705

.703 · 7~:3

HAUT t'lACH •

• PRISES DOUBLES ..;. HUB. AMNT

.5', '" 613 '" 61

.7')5

.70:3

.7'06

• 7~j4 ~ I 7~J:3 .,p .7Ct3 ~

.iQ!3

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.7'1)4

.;"c.l4 ~ ?RISES LAT. GAUCHES~ • 7~:3

.~

.705

.:-05

.71·)

.71.J

.71,3 • 7' 1 " .;"16

.• 71~ .7213 .714

.7'lj5

.7Q:3 • ;"0', .7')4 .701 · ;"~)~ • ~~j5

• ;"1):3 7' .7CJ3 :3 .702 " • (1):3

P) .7133 11 .7Q:~

HUB. A"/AL

• ~0:3 ;2 • 7~7-.3 .707"' 4 • il)'~

,; F'R I ::·E'; LIH. DRiJ I TE;* .(1)7

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• ~~)6 .7":):3 .;"~)~ .o?'? ,7~7' • ~'?8 .71:3 • ;"~j-) • 72'3 -5~'~

., . ., . ., ':l~

• • -- ,/j .. (

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.:"61 • 7"'~~ 1:37"5 · '? 31

1 •. ),?~

1. 15':. 1. ·)032

• ·:;~.3 .7"7'1 ~, '

• I lor:.

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~ !~ . ~:a5 ~ 11 .(1)5

'+ !-iI,IS. I~AUCHE

t'lACH ..;.

.7"1-j7 ~

.7'101'5 ~

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HIJB. DROIT ,;

05 ., 2 135 '+ .3 0'; ~

4 LJ~..;.

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:2 OS..;. ~:3 tJs..p 34 \)'5 ~

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MACH DE REFERENCE- .6019 TI"/-2"6.4 K

UINF- 231.109 M/S PIV- 1:393 ~lB

MACH PAROIS HAUTE ET SASSE • MACH PAROIS LATER.

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MACH DE REFE~ENCE~ .S~85 TI',/=:,2"7.1 K

UINF= 231.193 M/S PIV~ 1~52 ~lB

MACH PAPOIS HAUTE ET BASSE • MACH PARors LATER. * AILE A:;;'1{'

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1 • ,)~j~) • ?:31 ,9~7 .';.44 · ,4', · :::";~ .? '5( • ?-+ 7 , :3'? 1 • :3·,r3 , :~21'5 .411)

1. '52'3 1. 4'54 1 • ;:3~) 1,26"; 1 • ')\.0)5 1. 1)2', 1.")'5") 1 . ~)2'? 1. 1)(1:3 1.1)91)

, ·'5'? .:. ,~

•• _I

.?21 • '? 12 · :349 • ,?O~ • :3:3~

---------);2S

.. ,---------------_ ...

24

******** •• ~.**~*** • .,,*.* •• ~~*.. FICHtER AD135 N~CIT)~ 4 22/ 8/8~ 9H30 AS07 Ms.? I=0 R 2-5 ADAPTE ZD AD13~ De~ AD134 4' ITE -----------------~--------.--------------------------------------------------l'IACH DE REFERENCE= • ;'\)21' IJHIF= 231.11ilS 1'1.·:, -.

TIV=297.l K prv= 1521 Me *~~******~~***~***~~~~~*~*******~~****~**~***~*~~****~~***~*~~~~~*~~~~~~~~~~~i

.2 3 4 '5 6 {'

9 '~

1~ 11 12 13 14 1~ 16 17 19 19 20 21 22 23 24 2~ 2'; 2, 29 2'~ 30 31 ·32 '33 :34 3~ '36 .~~

~ (

3:3 '3'3 40 H 42 43 44 4'5 46 47 4:3 49 50 '51 '32 ~ ... J.j

54 55 ~.; ..... .J(

58

MACH PARors HAUTE ET BASSE ~ MACH PAROIS LATER. '" A I L.S H~~?

HAIJT

.70:3

.704 • 7'~:3 • (1)0 • 6'~'3 · 7'~n • (1) 1 • (~2 · 7~)2 .704 • 7~J2 .699 .701 .701 • (1) 1 .701 • (1) 1 .704 .704 • (~7 .706 .7\.j7 .7~7 .(~6

• 7~:3 • 7~:3 .714 o (1'; .721 .71 :3 .7~2 .717 .71'3 .714 .71'5 • :"14 .717 .717 .721 .11:3 .71:3 .713 .71:3 • :-(\3 .:-06 .;'0'5 • (1)'? .7Q'? • (1)9 • (1)'5 • (1)4 .104 .(1)4 .-:-133 • 7~:3 .700 · ';',7 • t5';'2

8AS

• (1)1) .(1)4

.702

.702 • 7~3 .N4 .7132 .(01)

HAIJT

* PRISES DOUBLES

BAS * '" '" * * S'~

• ~0 • 61

.701

.(1)0

.7~1 '" ~ '" ~

." P~ISES LAT. GAUCHES_

~1ACH

HU8. A110~lT

1 2 :3 4 5 6 7 :3 '?

10 11

.;'013 • 69'? • 6'~'? .700 .69:3 • 6'~:3 .~9a .697 .698 .69:3 .699

1'1ACH •

.~02

.~~2

.7'102

.7133

.704

.704 ,7e, .;'01 .700

., '" '1·) .. 11 • 12

• (1)2 .0',7 .697 .6'?9 .I'H:3 .700 .71n .702 .7~2 .0'?9

.7131

.7'1)1

.704 • 7~Jo .;'1)3 .;'13 .7'HI ; 710 .715 .707

HUB. A"/AL HIJ8. DRO IT •

13 14 15 16 1;' 1:3 1 'i1 20 21

• 0'?:3 • (1)1) .7~1 .701 .71313 • ';'?9

7:3 .• 7'J3

.6';'5 ;:

• PRISE! LAT. DROITES*

74 ;''5 7~ 77

.7,)4

.7'03 • 6'~7

;+

*' ~

. ., .. '3 4 '5 6 7 :3 .,

10 11

7 :3 .? • o';'~

.6';';

.0'?9

.713:3

.7(14*

.704

.701

.7~4

.7'34

.701

.701

.701

• ~.~7' .0·?9 .6·?5 · ';'~', .7CJ1 .6'?:3 .6 ?:3 .7'01 .7.)4 .7(1:3 .~~2 .700 · ~"'~ .;'~1 .703 .701

• HU8. I~MUCHE

1~ 11 12 13 14 1S 1'; 17 1 :3 1 '~ 21) 21 • (131)

.7~13

.71313 • 7~~) .7~1) .7~13 .701 .7'32 .7131 .792 .71J0 .701 • 71J~ .7CJ13 .701 .7131 .7132 .(1)13 .~99 .697 • 096 ,';97

.725

.71 :3 • ;',)9 • :-:;,19 .;'02 • ;'1)4 .701 .0'?'3

.;'5:5 • ;""39 • .~~:3 • '?26

1. Ij ';' 2

• ~,?,~ • ;',)0

• 6'~:3 .6?'5

1. 146 1.0913

• :363 .. .... · (~(' · 711

.1

7 :3 ';

10 11 12 1'3 14 15 16 17 1 :3 1 " 213 21 '':1"') .. -* Z:3

• 24 .. 2'3 ;+ 26 * 27 * ;::s ... ;29 * :3~ .. :31

.711 • ;'11 • 710 .71a4 • 71)'5 .7~7 .710 .712 .71·'3 .711 • ;'1 I) · 70~ • 7'J:~ • ;'0:3 .7'34 • ~:a3 • 7~4 .704

31

.;'1;)4

.70434

.70'3 .35

.70'336

.;'04

.7'0:3

.710

.712

.714

.711

.707

.700

.105

.;'02

.7CJ2

.;'02

.7~2

.7'02

.702 17~2 .~~~ .70:; .;'02 .7'~2 .7~2 .~~2 .701 .~'3:2 • 7'('~

.7C~

.702

.:-02

.7'IJ2 • 7'"~j2 .;'01 .:-031 .;'001 .7'»1 .71) 1 .701 .701 .;'1)2 .:-az .i~2

• 7~)2 .7~2 .7'"0:2 .702 .~02 • 7~):2 .702 • ;-~J2 .702 .7'"02 • ~1J2

24

• ~7~ .I£·3'~ • ;'42 • 3Ij,) .7'3( · ~~~ · ~~~ ·~H , ~:3~

1. ():::3 1 • ;j5~

• '?'3S • :3:37 • :3:-~ • :35:3 • :3~'5 • ,3"2 • :,4) • :3:3:3 • :335 • .321 · :~ I '5 • :383 • ~57 · ~:~~ • ;";:3 .;'% • :"'?2 • 7'5, • ;"2'5 · ~~7 • ~'5:3

1 • l?.s 1 • ~)~~

• '?22 • ,~'?4 • :::3~ • '3;"? • '~~? • ·::5'; .::4~ .:33:3 • :32'3 • :312 • ;"'?3 • 7'?,) • ;':31 • ~4:3 --.. • I I I

/26

2S

*.~*.*.*.* •• .;.**.**.~.;. ••••• *... FICHIER AD136 N~(IT)3 4 2Z/ 8/85 'H55 A907 Mm.S I30 R 2-5 ADAPTE 2D AD136 D!~ AD13S 4' IrE ------------------------------------------------------------------------------

3 4 " . .)

~

:::3 ··3'~ 410) 41 42 4:3 44 45 46 47 48 43 '39 51 52 53 54 55 56 5, 58

MACH DE REFERENCE= .5972 TI ' .... =295.:3 1<

UINF3 231.l9a M,! PI""3 1:39:3 MS

MACH PAROIS HAUTE ET BASSE .;. MACH PAROIS LATER.

HAUT

.S"S

.'39S .5',', • ~"S • 5',:3 · 5'", ',5,,7 .597 .5n .5,,8 .5,,7 • S'~05 .597 .5,,6 .5,,6 .5% • 5'~7 .5';';& .5';8 .5',', .699 .610)2 .693 .692 .69:3 .692 .695 .695 .69:3 .696 .698 .696 .~e7 .69'3 .696 .610)05 .697 .~96 .6110) .698 .69S .610)'3 .1')~7' .604 .69:3 .602 .602 .601 .60e .5,,8 .5,,8 • ~',7 • 5'~7 .597 .5',7 .5% · s',s .597

9AS

.5',6 · 5'~', .5',:3 .5',:3 .5',8 .5'n .~97 .536 .5'n .5,,4 .5,,6 .5',05 • S',05 .5305 .'3% .5',4 .5,,5 .S"S • 5',05 • 5'" .s'n .5,,4 .5'3:3 .5',5 .5,,6 .5% .5% .5',:3 .5,,:3 .5',8 .5',6 .5',', · S',', .5',7 .5,,7 · ~',8 • ~',6 .5,,6 .59'3 · S',5 .5','3 .5,,5 • ~',6 .5',05 .5305

'. s'n .~% .5% .535 .5',5 .5',5 • S',6 • 'S',6 .S"S .~34 .594 .5'34 .S'?8

HAUT MACH

* PRISES DOUBLES "' HUS. AMONT

5', .;. 60

61

.5',7

.5',8

.5',6

* ~ PPISES LAT. GAUCHES*

· 5'~:3 • S',8 • ~5'?" · ~~'?9 .609 .692 .692 · ';;92 .6es .600 • ·S'37 .594

.5'?:3 .5',',

.5',7

.5%

.595

.5',:3

.5',8

.5',:3

.5','3

.5'3'; • ~.?t5 • 5'3:3

.;

.;. PRISE! LAT. DROITES*

.59'

.5',7

.5'?7 • 'S'?6 .5',6

HUB. AVAL

:3

1 ~) 11

.5',:3

.5,,:3

.597

.598

.597

.5'37

.597

.598

.59:3

.5',6

.'5%

• ·S'~7 .694 .606 . .695 .69', .612 .613 .619 .6S" .6e9 .614 .~08 .604 .~92 .5'37

• 5','? .5',7 .5'?..\ • 5'~4 .S'?2 .5'32 .5?5 .59:3 .S'N .5',6 .5'?8

.;. HUB. GAUCHE

~

• 'S'?:3 .5',5 .5n

5'~o:.

,5'38 .5·38 • S'?6 .5',5 • 5'~5 • S'~6 .5',6 .5';'5 .5,,4 .5,,5 .5',:3

PP.I3ES COL

• !~52 • ,5';',; • :-,? 1 · :35'(

1. iH'~

1.J41 • '?23 • aloJ 1 .6'?4 · ;,32

.;.

3 4 '5 6 .. , :~ ':'

10 11 12 1 :3 14 15 16 17 1 :3 I'? 20 21 22 2:3 24 2~ 26 27

.6~3

.602

.6032

.539

.599

.';~9

.6@2

.604

.694

.604

.6032

.602

.601 • 6~J0 .538 .53~ .'597 .5',7 .597 .598 .5',:3 • 'S',9 .5',7 .608 .601 .602 .604 .605 .~0:3 .~01 .609 .598

NACH •

HUB. DROIT ;;.

:3 4 5 6 7'

.598

:3 ';:I

10 11 12 13 14 15 16 17 1 :3 1 " 20 21

.59:3

.S9:3

.5',8

.59:3

.59:3

.598

.5,,:3

.59:3

.'598

.5,:3

.5,,:3

.5.,:3

.597 • 5'~7 .597 .'5'37 .597 .597 .5';';.' .S~( .597 .597 .5'37 .597 • 5'~( .597 .5',:3 .5 ?:3 · S'37 .5'"

,. . 28 ,. 2',

• 5,,:3 • 5',:3 • 5',:3 • 5',:3 • 59:3 • 53:3

3:3 .597 * :3':' .5':7 :+ 40 .5',7.;. 41 .597 .. 42 .597.;. 4:3 .597.;. 44 .597" 45 .5',7 ,.

t'lACH

, St5', .5:33 .61'3 .6:39 ,1:)7':3 .642 .':;91 '.5:34 , .,,~

• ~.~IJ

• :3:31 • :3:35 • :"6? .7:3:3 .~24 .715 • ;"LJ5 .701 .701 .6% .6,3 • ,-5:3:3 .05:30 .~71 .55';' .5";:3 .~24-.tE7"'l .664 • ~:35 .';11:) .5'?5 .3PJ • '~3'~ · ~'~;.' .7"5:3 • 7"4~)

-. .., ... ., ..;"

.;"21 • 711 · (~:3 • ';';':3 • ~'~2 .6:30 · ~~.? .~r5'; • r55:3 • ';:3~3 .0S7' ,"£24

/27

26

~~~~~~***~*~*****~*~*~~*~~*~** FICHIER AD137 ~~~(IT)= 1 22/ a/a~ 10H25 AS07 M:.~ I=0·-30'+ROT.3a') R 2-5 NON ADAPTE AD137 DE AD44' l' ITE PAROI:3 RECTILIr:itlE:5 +30' -------~~CH-DE-REFERE~CE:-~597;------~I~F:--;;~~~es-~~s----------------------·

TIV=3131.0 K PIV2 1393 MB *~***~**********~*~~~~**~~****~*~~*+~~~*~~.~*~**~~*~~~~~~~*~~~~~~~*~~~~~~~~."

.. , ,3 "

1 ~) 11 1Z 13 14 15 16 17 1 :3 1'? 213 21 22 23 24 2S 26 . .,~ ... ,

MACH PAROIS HAUTE ET 9ASSE

HAUT

.605

.61H

.6131

. 597

.595

.5'?8

.5',;" • 5',8 • 5',:3 .5',:3 .5% .594 .5',5 · 5',6 • 5',;" • 5',:3 S'~':'

SAS

.S'H

.5',5 · S',,, • 597 .599 .61313 .~97 .5',7 .59:3 .S95 .S'?6 · S',,, .59~ • S',7 .59:3 .5',7 .59:3 • S'?', .59', .05013

HAUT

• PRISES DOU8LES

.'S'"

.598 • 'S',7

.5'?8 .. ,~ .. • ·oJ ~ I

.601 • • PRISES LAT. GAUCHES.

72 7'3

.5,,9 • 60~) ,~i02 .613:3 .6Ij', .613 .614 .614 .614 .~~? .602 .5;-8

• .s'?7 .601 .61)2 .61313 .59', .6136 .6134 • 604 • 6~:3 .6032 .~~4 .6t16

* • PRI3ES LAT. DROITES*

74 75 76 77

.61313 · ;'?7 .5',:3 .5',7 • ·S'?9

· 5 ?:~

MACH PAROIS LATER.

HUB. AMO~lT

2 3 4 5 6

:3 '?

10 11

.5"',

.~99 • .59';& .'3'?8 • ~9:3 • 5'~8 .59:3 .~9S · ~',;" • 5',:3 .S9:3

HUB. AIIAL

4 5 6 .. I

:3

10 11

.6131 · 6~2 .602 .6;):: .6'32 .';02 .6~2 .~03 .~04 · 6~j2 .602

r1ACH •

:3:3 • ~~5 -+ 34 .617)4'" :35 .6'j4 * .36 • r5~3 .. :3, .1'517):3 • 3:3 .603.;. :3', • ';~3 .; 40 .6134 ., 41 .6134., 42 • 60~ * H .6iJ3 '" 44 • 6132 '" 4'5 .601 ..,

HUB. DROIT .,

.2 • 59'? ~ :3 • 5'~', ~ 4 .5',:3 .;. 5 .5'?:3 :0-

6 .5',:3 • "( .59:3 * :3 .59:3 ;(-'? .5',8 ;-

113 .59:3., 11 .59:3" 12 .5',8 .,

.602

.1'5132

.613:3 • o~):3 .1'50;" .611il .611 .612 .612 .615 .616 .61 :3 .617 ,I'jZl .61:3 .61';0

• QO~) .600 .59', .600 ,.59'? .6013 .6013 .60:3 .60S .605 .603 .606 .604 .61()2 .602 .603 .601 .601 .601' • .6013 .601 .601 .6133 .604 .60:3 .613:3 .601 .601 .6131 .6132 .602 .6131 .tS~2 .602 .602 .602

• 6J 1 .613:3 .614 .61'5 · 61:3 .623 .~24 .623 .621 ,';21 .623 .~17 .611 .6139 .~iJ1 • ';'Q2 .5'?5

.5'?7

.5'?6 • .5';'7" .5'?'7 • HUB. GAUCHE 1:3 • :9:3 +

• ~ 17 • 1'51', .61 :3 .61" .1'517 • 61', .616 .1'516 .616 • 614 • 1'511 .6113 • 613', .~13,? .606 .61)4 .601 .601 .s'?'? .5':( · S',5 .592 .58;" .5813 .572

. 604

.60:3

.665 · 6'?~ · :301

1. ~27

• 5'~'? • 60~) .s'?'? .6031 .6as ." .6J5 • ";~:15 • ~ ~J:3 .6031 .601 • ~~):3 .6.£I~ .602 • 6~)t 1~~1 .61;'6 .60~

1 • 1)6 • '~~J

",,~ ., .

z . ,3

1 'J 11 12 13 14 15 16 1'7 1 :~ 19 213 21

.612

.612

.612

.606

.,;~.;

.60:3

.618

.612 ,";12-.611 .610 .0510 .6'J';' • 6~:3 .6~4 • ,';~:3 · ';.3:3 .684 .604 .605 .617)5 .~;)5

.604

.0'37'

.60:,

.6a'?

.0511

.611

.05 1 Ij

.6J:3

.~06

.6(l6

14 .59S ~,

15 .5';':3 " 16 .59:3" 17 .5'?:' 1:3 ,5'~:3 1', .5',:3 2~J • ·5',:3 21 .~'?7' 22 .5':7" 2'3 • 'S'?7

~,~

- 0'

35

.5';'('

.597'

.5'3:3

.5,,:3 ,5',-:' .:; ?::: , .5'~:3 .5',:3 ,5'3:3 , 5'~:3 ,5'3::: .5'3:3 .59:3 • 'S',:3 • ::-;H3 .5'?:3 .5'3:3 .5'?:3 .5',:3 .5',:3 ,5'?:3 .5',:3

'3 4 5 6

10 11 12 13 14 15 is 1:" , " l.':"

1'" 28 21

,N

') , -'=' ., .. -' .,:,,=, -"

:' ~ ~ : ,~~; , ~:~~ , ~;3 ~ t ~~'~ .':.j7" · :- ~ ~ , ~'3;~ · ~:~:~ • ,~-l:~ • ;o-l · ;- ~~ ~~ .

• , j;; -~, · -. ~, , : :'~):3 • 7'~j:3 .783

• r5~ ~ , ,-£..1 ~ .0:) lJ , ~'?'3 • 31 ~ · ·.~~2 • 312

• ;"' .. ? ...... .., • I";' ........... • I ;,

.7?1 · - 2~; · ~l; · :"~);-· ;".): , ';:,::3 · .::~~ • ~7"J ,,:>,=,Ij

.rSJ..l ,':r5'; .-:..; .. )

2-7

*"'++++ ••• + •• "' ••• "'+."'."' •••••• +* FICHIER AD139 N~(IT'~ I 22/ 8/~~ laH4~ AS~7 M·.~ I~0(-3a'.ROT.30') R 2-~ ADAPTE 3D ADIJ8 DE AD'?!:3? l' ITE ------------------------_ .. --------------------------------------------_.-------

MACH DE REFERENCE~ .5985 TI'/=:l~O. ~ K

UINF~ 231.1~8 M/S PIV~ 1392 ~!9

MACH PARors HAUTE ET SASSE ;I, MACH PAROIS LATER.

7

HAIJT

.15015

.6~5

.~~1

.5',7 • 5',~ .5'" • 5'" • 5'3:3 · 5'?9 .6~0 .59:3 .5'37 .'5',9 .15~~ .';0~ .6~~ .5',9 .5',9 .5',9 • 6~2 .6~1 ,,;e2 .6~2 .6~3 .6015 .6~5 • 6~)7 .607 • ~YJ8 .606 .6~9 .607 .6~8 .6~6 .6~7 .-5136 .-50, • 6~37 .611-) • 6~'~ • ~'J';' · 6~', .6~7 · 6~4 .6133 .~a2 .6134 .-5'.14 .6134 .602 .-502 .15130 .6131 · 6.)~ .6')0 .5',7 .5'H .589

--

SAS

.5'?1

.595 · ~',5 .5'37 .5',9 .6~1 · 5'~', .5'", .6'.11 .597 .597 .597 .597 .599 • 5',9 • 5','~ • 60-J .6a~ .6~~ .602 .60-) .597 • 5'36 .6ao .613:3 .602 .602 .6a~ .601 .601 .59:3 .6~2 .602 .6131 .6~1 .6'.11 .600 .6013 .61313 .6013 .599 .5','3 .5'?8 .5'~:3 .598 .599 .601 .602 .501 .61313 .'59'? .598 .6~1 .6·)2 .602 .6,)2 .6133 .6'.1S

-

;I,

HAUT MACH

PR I :~ES DOUBLES ;<, HUS. A~!ONT

• ~'37 .600 .6131

• '5';"? • .6013 '+ .599 '+

.600 2 .5'39 :3 .598

* PRISE! LAT. GAUCHES* 4 .598 5 .5',8

.5,,:3

.6~~

.1502 • ;S~0 • ~.)2 • ~ja4 .O:)~3 .6134 .606 .'::01 .602 .5"1

'+ .5'?1!i * .6.)2 *' .613:3 * .59', *' • ~'J1 ,. • 6~31 ;; .601 '+ .~02 * • 5'?3 ., .601 * .59', ., .l!i1il4 +.

:;.

6 .598 7 .598 :3 .59? " .598

113 .598 11 .599

HLIS. rWAL

.602 2 .602 3 • ~a2 4 • ~a2 5 .601

PRISE! LAT. DROITES* 6 .~al

74 75

· 6.)~ .5'?8 .5'37 .5',', · 5'~8 .5',7 .5'?9 .5'?6 .598 .5'?:3 .5'3:3 .597 · ~.j5 .59:3 ,~6S .'5% 0667 .6131 .61~ .6132 .613 .601 .~14 .602 .611 .6133 .610 .6.)2 .6113 .6131 .614 .5'", • 6~9 .59', • 6~)4 .59:3 .6>33 .600 .6')0 • 6Y)~ .6133 .5,,:3 .598 .6133 .5:39 .61)1

PR X3E'3 COL

.615 .. ; 1.1)64 · ~.~~~ , ,,~::1( • :302 .7"9!5 • :36:3 • ~'~2

1.02:3 .6:32

--

* f .~a2 ;;. :3 .61:34 ;;. " .6134 ;<, 1~ . ';:02 ., 11 .6al

.~

:3 4 5 -

.6135

.6as

.604 ;~01 .601 .60:3 .6VS .~a6 .6137 .-51315 .~a4 .6as .604 .6134 .6.n .601 .6al .-5131 .6131 .6132 .~~2 .60:3 .~01 .604 .604 .6135 .6'.17 .6ae .6013 .604 .6134 .602

MACH '"

• ~01 • · ~el * .~al ;; .~131 ., .6131 '+ .601 -+ .600 ., .601 -+ .601 ;; • ';131 ~ .';13~ ;; .600 '+ .598 *'

HUS. DROIT ;<,

• 5','~ .59', .599 .59:3 .5',:3 • 59'~ .'B" · 59'? .'59', • ~9', .593 .539 .S,9 .59'3 .59:3 .5',8 .53:3 .5',:3 .5',:3 .'599 .'599 .599 • '3,,'~ .5.,9 .5',', .'B'? • 'B:3 .59', .5"'~ • 59'~ · 5'?'~ .599 .5',9 .'599 .599 .599 .5'3:3 .'5',', • SSI:3 .5',:3 .598 .59:3 .5'?:3 .598 .59:3

2 3 4 5 <5

37

"!ACH

.'570 · 5:31 ,';.2:3 • 6:31 • ~;3'J .651 • ~: 11 • 5'~'~ • 3:3iJ • ;::~2 'j'.,'" · '.'.-

• 7';~ ~ . .,.~

• I oJ ...

. 710

.712

.702 • '::'~8 • ";'~:3 • 6'?3 .6':1 • r5;32 • ';:3 ~J .- .... .r, .. ..;.

.5~1

.5:31

.-527

.~~:3 .:~.., · ,~ .. -

.64'?

.62'5 ,,-517 .303 • :3','~ .... ~ . ., • I , _

.740 • 73~) .i24 .7'21 .71 r; • ~~J~ · ';','? .-5'35 .-5?O • r5,3~ ,~67 ,';r5'; • 66~j , ':'4» t ~r3~) .';:2.7

129

"'*************************.*** FICHIER AD139 N0(IT'= 1 22/ a/8~ l1H 0 AS07 M=.a I=0(-30'+ROT.30') R 2-5 NON ADAPTE AD13~ DE AD44~ l'ITE PAROIS RECTILIGNES + 30' -------~ACH-DE-;EFERE~cE:-~8e;;------~I~F:--z;i~io9-~~S---------------------,·

TIV=301.2 K PIV= lS51 MB ~**~~~~**~*~~*~~*~~~~*~ .. ~~~~~*~~~ .. ~~ .. ~~++.~~~*~**+.~~+.*~~~~**~~~~+.~~~~~~~.~~.~"

2 3 4 5 6 ., ,


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1. (15,3 • '?25 • :3.) 1 • ~'?:3 , ';.3:2

.5"S

.S9:3

.'H:3

.59:3

.597

.5'?:3

.5'::3

.59-;

.5.,:3

.5::3

.597

• .;>a~) .6>ata • 6il~)

.• '5.,:3 • ·5'37 .599 .6>a0 .60e .6.) 1 · .; ~)~) • ~5'?9 .6u0 .59', .59', .53', .59:3 .5,,7 .'597 .597 .598 .5';8 .5'39 .597 .599 .60ta .601 .602 .6133 .6132 .6013 .599 • 59'?

r',ACH ;+

.5',', • 5','~ .5',9 ,59', • 59'~ .5',', .5',', • ..;:.JL) .'::00 .600 .5',:3 • '5'?:3 .5',7

HUB. DRIJI T ..

7'

• ::'?7 .597 .5';'7 .5',7 • 5'~7 .5',7 .597 .5'?7 • 5'~( • ~,?;, · .S':? • 5'~( • S'?? .5',7 I .5~( .5'?7 • ::'~7 • :"?7 • .S'?7 • ~,?7' .5'?7 .::'~7' .5·?7 • '5'37 • 5':'~ • 5'~7 .5'?7 .5',7 .~~7 .~97 .597 .597 • 5'~7 • ·S~7 .597 • 5'~7 • '5'?7 .5'?! .5~7

• 5'~7 .5';'7' • S'~7 • 5'~7 .5.,7

,. *'

" 1 i.) ,

11 12 1:3 14 15 16 17 1 :3 !';. 2~)

21 .,,-? -'-

.575

.5'31

.639

.6,,0 • ~'~7 • ·';:36 .. ""'" .':IP:I{

.6:31 • :317 -"'., • ( .j(

· 736 • ;" 1:3 · 6'~', • ~:37 ,1'j:32 .t5~~ .~~s .67:3 .~77 .67', .6';"'5 .6-;-:; .67'(' .5";7 , ·5~:3 • ~,~4 • ~,~6 .6,'5 • ~,3'? • ~:S:3 .72:3 .312 .702 .6?S

.6';"5

.675

.':1 .... , -:";-:3 .S7'S .';71 ,'::71 .';~1 .66:3 .r:.~2 • ":'';:3 • r:,·5S .";'42 .';5~ .62',

34

***********.*****.***.****.*** FICHIER AD145 N0(IT)~ 4 22/ S/8~ 17H15 AS07 Ms.6 !2+2 R 2-' ADAPTE ZD AD14' DE AD131 4' IrE. ---------------------------------------------------------------------------.~~ MACH DE REFERENCE= .5959 urNF. 231.10e M/S

2 :3 4 , 6 7 ,~

"

"

113 11 lZ 13 14 15 16 1;' 1::) 1 " 29 21 12 23 24 25 21'5

TIV=297.1 k PIV~ 1391 Me

MACH PAROIS HAUTE ET BASSE * MACH PAROIS LATER.

HAUT

.5',:3

.5',9

.5',8

.5'?t5 • '5',S .5',:3 .5',7 .5'?7 .5'n .5',:3 .5',6 .5":14 .5',6 .5',6 .5',6 • 5'~7 .5,,:3 .690 .599 .60ta .59', .601 .603 .6134 .608 .6136 .609 .60:3 .611 .6~:3 .612 .60:3 .611 · 6~:3 .610 .609 .611 .610 .613 .610 .610 · 61~) .607 .604 .603 .601 • 6~):3 • 6~)2 .601

5'=-':' .5',', • 5'~'3' · S',', • 5'?'~ , S'?8 • S';'4 .'591 .5:36

BA:;

.'93

. ,'n • 5',6 .,% • 597 • 5,,8 . 5% .5',5 .5',6 .sn • 5,,4 .594 • 59:3 .5',4 • 5',5 .5"4 • 5"4 • 5,,3 · 5,,2 · 5',4 .593 · 591 .589 .5'H .592 .592 .5"1 .5n .592 .59:3 .58', .592 • 592 .591 .5',9 .592 .5',0 .5',1 .5',1 .591 .5'?1 .5'H .5n .59:3 .592 .592 .592 . 592 .5',:3 • S'?S .5',5 • '5',4 .5'?5 .5',5 .5n .sn .591 .5:3:3

HAUT ~lACH

..; PRISE! DOUBLES • HUB. AMaNT • * S'?

..; 6,;)

.. 61

.5'?6

.5'?8

.5',7

,5915 * .'5% • .5',5 '+

1 .5% ;2 .5',5

~ * ..; PRISE! LAT. GAUCHES •

'3 .59~ 4 .5'" 5 . 5',5

..;. 62

.. 6:3 * 64 ... 65

.5',6

.5',9

.6".10

.599

.6132

.603

.603

.-505

.606 • 60~ .5',13 .58',

.5'?6 •

.598 •

.5'n •

.594 •

.593 '+

.5',5 '+

.5,,4 ..

.S'?S *

.'5-:3 •

.592 .. • ·S;'6 * .598 *

6 • 595 7 .59~ 8 .594 '? .594

10 .594 11 .594

HUB. A"lAL

.598 ~ .597 3 .598 4 .598 ~ .'397

..; PRISES LAT. DROITES. 6 .599

..,.

..,.

9:2 ',3 ':'14 '35 '?6

.5',7

.597 · 5',;' .5'?5 .5',5 .5'?8 .606 .6".19 .612 .614 • -51;3 .61:3 .616 .614 .613 .-517 · 61~) .604 .602 .5'?7 · 5'?~3 .5·?6 .5:37

• ·"55';' .6'?S · 7'~6 · '3>5.3

1.~:121

.5'?:3

.'5%

.5','3

.5'?2 · '5,,1 .5:3:3 .'5',0 • ,'5:3:3 .58', .5',0 · 59~) .'5n • 'S'?! • 'S," • 'S',0 .591 .5,,2 .59:3 • S'?:3 .5'?3 .5',4 • '5:3', .5:3:3

1. ~j57 • ?~3:3 • ;-'?'3 • ~'31 .631

7 .598 * :3 .59', * " .598 * 113 .597 * 11 .597 * ;t HUB. GAUCHE

~ .

~ ,. :3 "

10 11 12 13 14 15 16 17 1 :3 1 ';' 20 21

.60~

.604

.605

.600

.'500

.60~

.-504

.606

.607

.61,)6

.604

.603

.602

.6131 • S9:~ .597 .'597 .5',7 .5',:3 · S',::.5',', • '~0~) .'59:3 • 6~ 1 .602 .>503 • tS0~ .606 .>505

30 .60:3 31 .601 "32 • S':8

MACH ..

:33 • 597 ,~

34 .596 .. 35 .595 .. 36 • '396 '+ :3( .5,6 .. :3:3 • '5',5 .. :3', .594" 4~) .5'H" 41 .5'34..; 42 .594 ;t

43 .5',4 .. 44 .592"; 45 .5-::3 ..

HUB. DROIT ..;

:3 4 5 .; 7 :3 "

1 ~) 11 12 13 14 15 16 17 1 :3 19 1~ 21

.5';17

.5',6

.597

.597 • '5',7 .597 .5',7 .5'?7 .597 .'597 .596 .597 .5',6 .5',6 .5% .59>5 .5',6 .5',6 .5 1?6 .596 .5',6 .5',7 .5';;:.596 • '5',7 .596 .5',6 .597 .5'37 .5',7 .5',7 .5',7 .5',7 .5',;.5'?7 .596 .5',6 • :"~6 • 5',6 .596 · 5'?6 .5',6 .596 .596 • 5'~~

1 "

.,

34 35 36 37

• 'S~,; • 'S~, · ~1; I .~~~ , ';4;,

· :?: ,SH · .;;~ .n:

1.0'?l · :3'~~ .:33')

· :'~~ , I ~? ~",

" 01';'

• 7'3~ • 7"1~~ • ~Z4 .71:3 • 7'0'~ • 6'~e · ,;a~ .6('5 .552 · ~,;~ • .; 15 • ';.;5 .623

.4;3': • 34'~

1. 07"? ! . ,)12

I '?24 .::r3'? • :3') 1 • ... ·32

.7'J'? ..... c::'

• I j.J -':Ie'

, 05?~ • ~7'~ .,,'=', .-5';.) ....... • .~;.j

• .;:c;~

13(;

~~;;*~;;*~*~*;;;; ••• ;;;;*~~*;;~*;;*;;** FICHIER AD146 Ne(IT)~ 4 a3/ 8/85 9H50 AS0? M~.~ I~.2 R 1-4 ADAPTE 2D AD146 IlE AD145 4'ITE. ------------------------------------------------------------------------------MACH DE REFERENCE= .5936 UINF- 231.1e8 M,S

TIV=297.e K PIV~ 13?3 Me ~*~~~*~*~~~**~~~**~~~**+.~*~~~**+.+*~*~+~*~~,~~~*~*~***~*~*~ .. *.~~~~~~~~~.~~~~~~~


HAUT

.s',S

.5'?6

.5St'3

.5';3

.5n • S'34 .s'?4 .5'34 .s'?4 .5'?6 .S9S .5',:3 .5',5 .S'N .5',4 .S'N .S'?5 .5',7 .5',7 .5',:3 .5',7 .5','3 .681 .681 • 6"34 .610)3 .607 .613:3 .611 .68:3 .611 .6'3:3 • ,:,~J'? • ,.;:~)S .6137 .6tl5 .r5~7 .6.)6 .6·3', · -::·37 .~07 ,~~7 .610)4 • ,; ~jl.) .6tl0 .5'?'? ,,;.a2 .602 .5'," • 5',5 • 5',5 • S'?6 .5',6 · :':6 .5'?5 • S'?2 .5:3'31' .5:34

-_ .. ,--

BA:3

• S', 1 • 5',5 .5'3:3 .5',2 .5',3 .5'14 • '5'33 .s'n .S'N .5',1 .5',1 .s'?! .531 .sn .5n .5',1 .591 • S', 1 • S'?! .5'3:3 .'3',2 • 5',1 .5:3', • '3:3', • '38:3 .58:3 .587 .53') .5:3', .S';h) .5:36 .530 .5:3', .588 · 5:3:3 .58:3 .387 .587 .5:37 • '3:37 .5:38 .58:3 .5',tl .s'?! .5':11 .5n • .~92 .5n .'3n .5n .5n .5',1 .sn • 5'?'3 • ,5'? 1 • '38', .5:36 .5:32

HAUT r'lACH

PRISE~ DiJUSLES * HUB. AMONT

• '5',3 .596 • S',s

f 5'?:3 * .5'H ;; • ·s',tl ;;

PRISE3 LAT. GAUCHE9;;

.5',4

.594

.5,?:)

.59:3

.592

.5'?4 Q ·597 .5'n .5',6 .598 .6')3 .6') 1 .6tll .604 .6·38 . 5',5 .5:37

.5'32 * • S·,6 ;; .5n ;; .5,,·3 * t 5:3'3 ~

.5'?2 *

.5',1 +

.5·,1 ;;

.5"tl ;; t S'?;.; 1io

.5',3 * · S',s *

*'

6 .592 ~ .5',2 :3 .591 ., .sn

l~ .::n 11 .5n HUS. A'./AL

.5'36 2 .5',6 3 .5',6 4 .5,,6 5 .S"S

PRISE3 LAT. DROITES* 6 • 5,S

74

( I'

.S'?5

.5':4

.5',5

.'S'N

.5'?:3

.5',7

.6~3

.606

.6tl8

.612 • IS 17 · I; 17 · ,513 d)10 • i5Q9 · ,; 1:3 .6tl:3 • t:i8 1 .6~2 · 'S',S .5% .5,,4 .%S

7 .5"S • S'~'5 .S'?3 .591 • S'?tl .5:3',

* :3 .5',7 ;; ., • S96 ., H) .594 + 11 .5,,3

.5:3:3

.5:3', " HU8. GAUCHE

.5:35 ;; • ;:36 * · 5:3'( ~ • 'S:~:3 ;; .5:38 + .5:3', ;; ,5:3'; ~

,~:3;"· ~

.5:3', * S'~·~ +

.5'?'': * • 5',1 + • 5'? 1 * • S:35 * .~8:3 *

"

1<1 11 1·') 1;) 14 1'5 I':> 17' 1 :3 1', 2tl 21

.60:3

.602

.602 • ·59:3 • ~'3~3 .600 .602· .6;)4 .604 • ~~:3 .6'32 .601 .601CI • 5'?'~ · ;',,.; .595 .::9S • S'?5 • S',5 .5% .5·3;; • S'3? .5',6

.~S3 1.g~:~ ~ 14 .5~8

.S~J .'~11 * 25 .5~9

.;"~2 ,~~3 * 26 ,~al

.:35'~ .68'3 ~ 17 .~a2 1.015 .~28 ;; 28 .6134

~ 2'~ • ~.a2 ;; ·310) .05130 +31 .5',', ., 32 • S',5

r'lACH * :33 ,5';4 ~ :34 .5n • 3S .5n '+ 36 .sn '+ .37 .5931-3:3 • 5'~2 * :3', • ~',Z -+ 4~ .591 '+ 41 .5',2 '+ 42 .. 5',3 ..;. 43 • '5'31 '+ 44 .598 + 4'3 .5910) ;;

Hue. DRljIT *

:3 "

10 11 12 13 14 15 16 17" 1 :;: 1 '? 20 21

.S'H *

.594 ~

.594 '+

.594 *

.594 ;;

.594 "

.5'H .,

.594 *

.59<1 ;;

.'594 '+

.594 ;;

.594 ~

.5'14 ;; • 5'?4 ~ .:94 -tit

.5'014 +

.594 .,

.5?4 +

.'S'N +

.5,?4 ~

.594 +

.5'014

.':94

. 'S'N

.5',4

.5·,4

.5',4

.514 ~,? .5'?4 30 .5·013 31 • S'~4 ~'2 ,5'?4 3:3 . 5'~4 H .S'?4 3:' .5':r3 3>5 .5'N .37" •. :',4 J::: • 5'~4 3'? .5',4 4(1 .5'?4 41 .594 042 .5',4 43 . 'S'?4 H .5·,4 45 .5',4

17

22 ., . ., -~ 24 ~ ... -.~

26

:.;t .1 ,,:,. .. " .. '

.57"', • ';~J6 "~

• ,=,,~ I' .61·,

.516 • ~,?'05

1. 010 · :3',:3 .7:"? .762 .735 • 7"2:3 • 7"0';1 .7"08 .~~ .'=' ...

• ";'?2 • ~;3'? .07:3 .67" 1 • -5S'? .552 .567" • ,.;:.) 1 • ·-5·?6 .057 , ·57..1 • ·5.~:Q .4::,2 · 374

1.21 "3 • ',:3:3 • :3·50 .~Q:3 • i:::'~ ~~o::'

• " .. I ~ ... ~

.' .. II

.712

.6;':3 I ~,?2 ,,.;:~O

.6~4 • ";·3~ .6";:1 • r:~25

/37

2 :3 4 '5 6 ;' :3 "

10 11 12 1:3 14

, 'I '5 16 17, 18 1 '~ 21) 21 22 23 2~ 25 26

:37

36

MACH PAROIS HAUTE ET BASSE it it

EII=t:~ it it

MACH PAPOIS LATER.

HAUT

.6~1 · 6~j~) • 5',1$ .5n .,5'H .5':3 • S',3 .SH .S'N .SH • S'H .S'?I.-) .5'H .5'?2 .S'?3 .S'N • S'?.; .5,3 • S'?', · 6~~ .6131 .6~S • 6~i8 .6.)9 .613 .612 .616 ,';17 .1'5:::0 .61'3 • ~2'3 .61 '3 .621 • tE. !:3 .~2e .61 " .621 .61 :3 .620 .~17 • .; 17 .616 .61:3 .611:) .60', .6~( .6~7 .6~S • ";~j2 • 5';':3 • S'?7 • S'::] 'P"

• 5'?~ .5:37 • S:34 .5,'::-.5'~

BAS

.587 • 5',~) .5',1 .~n .5?4 .5'?5 • ~'?:3 5'~'~

.5H

.530

.S'H

.5',1

.5',1 I S'?2 • S'?:3 .5n .5'?3 .SH .S'N .S?4 .~n . 5n .5'?13 . 59:3 .sn .S'?:3 • '5',1 .'3n • S9~J • S'? 1 .5:3:3 .5',1 • '5'?~3 .5,,1) .5'?0

• S'? 1 .sn .5';'1 .5',0 .~'H .'5n .5';':3 .5'?5 .596 · 5% .5';'5 .5'?6 .596 .~97 .5'n .597 .59:3 .5?:3 .598 .5'?8 .601 • 6~)S

HAUT

* PRISES DOUSLES

· S'?3 .5'?4 .S'?2

.5'?:3

.5'3:3

.5';'7

~lACH

it HI.lB. At'10~lT

., PRISES LAT. GAUCHES*

2 3 4 S 6 7

.595

.5H

.5',5

.5'H

.53:3

.S3:3

.5',4

.5H

.593 • S',:3 .5.,3

.,

.5';'4

.S'?'3

.5'?:3

.5';'9 • 6~j:3 .612 .614 .614 .61 :3 .604 .'5?3 .5;'4

· :'~2 .5';'5 • '3'?6 .'S'n .5'?6 .S'N .5'?4 .5"S .5'N .5',5 • SS'?:3 • 6~i0

:3 "

113 11

HUB. AI,IAL

* PR[SES LAT. ~ROITES •

2 :3 4 '5 6 7

.5',7

.5',7

.5',8

.6130

.6al) .5',',

.5',:3

.., .5'?:3 • S" 1 .5?'5 · :?:3 • ';~j'; .61:3 .616 .622 .':'2~ .628 .'::25 .'::24 .... , ... .1j..:,.J

.6:N

.617

.61·)

.6~5

.'5';':3

.5',7

.%"

.~61

.o::n

.797 • :~;;5

L.022

· 5';'4 .'5'?2 • 5'? 1 • 5'?~ • 5'~~ .%', .%" .5:B • 5'~~ • 5'?~ .5:;:3 • 5;3'~ • 'S'?13 .591 .5';'0 .5'?\) ,5'?3 .5';'; • S'3'5 .5'?5 • S',6 • ~~01 5':"~

1.06oa · ',,,,0 .7?1 .6:39 .62',

• S3', .600 .5;";' · 5,',

* HUB. I~AUCHE

2 :3 4 S 6 7

27'

.6L3

.611 • ~ 1 L .6~4 .6.)S .~08 • ~l~ .6L2 .613 · 61 ~1 • 61 ~j • ~O'? • '::iJ:3 • ~~J6 • '::~j1 .o::",~

.'S~'? • S')~J .6oae .681 .6CJ:2 .";~3 .6'31 .S~4 • ';\oJ~ .607 .6>J" .610 • 68:3 .606 .6134 .';02

t1ACH ,.

.J:iO~

.5',:3

.5',7

.5'?:3

.597

.5% • 'S',S .595 .5'?':) .597 .5',4 .5','3 .592

HUB. DROIT ""

:2 :3 4 S 1$ 7 ,~ 'J

"

., . ., -""

•.. .., ';'.j

.34-?S . .., .-.;.~

37

.5',3

.5.,4

.5":4 • '394 .5'N .59:3 .5'?:3 .5'3:3 .59:3 • ~'?·3 • ::'~:3 .594 .5?4 .5'?4 .594 • S'N .5','3 • ~·?·3 .5?3 · :;,:3 • .5.~ 3 • :'·~·3 .::;':3

• 5';"3 • 5'?3 .593 .59·3 .'S'N .5',4 .5';.4 .5N .5·?:3 • S'N · 5',~ • 5'~:3 • 5~:3 .5','3 .5'?:3 .53:3 .S93 .5'?:3 .5'?:3 .59:3 .5'?:3

~

'"

" ,.

AILE A%,

'.,~

'-'

, S:: .. } · :::;~ • ~11 '';''.') · .;:~ 157"3 · :~3 • -1.~ 3 , 2·?~

1. ,) 17 • .~ 11 .%3 , 7'~~ • ;''31 • 7'.~.~ , ;--~3 .7'14 • ;'I,j • ~~)S • ;"IJ! • .~.? t • ~,~.3 -., ,':Ii ..

• Sr:.2 .5;"; ,';1: .-:.J..)

' .. . ,:,.;, · ::.:;~ "" · ..... ~

• -1.? 1 • ·37·?

1.22';

. '. • .j~ ~

• .;~i) • :.~11 ........ ., .:-.j .7'71 .,,-· "

• ;-.:1'? • ,;?2 · ~:,j • ';~2 .': ..... · .;~, • .; 3l

/3? ,1

37

***.* •••••••••••• *.** ••• ***... FICHIER AD148 N0(ITj= 1 23/ 8/85 10H40 AS07 M~.~ I~+2(1.5+ROT.3a') R 1-4 ADAPTE 3D AD148 DE AD?122 l'ITE. --------------------------------------------------------------------_._--.-----

"

10 11 12 13 14 15 16 17 18 1 " 20 21 ;2;; 23 24 25 26 .-:.-,

MACH DE REFERENCE~ .5936 TI ',/::300.6 K

UINF~ 231.108 M~S P I ', ... ~ 1392 NB

NACH PARors HAUTE ET BASSE NACH PAROIS LATER.

HAUT

.601)

.5'39

.5':15

.5n • 5',1 • S'~:3 • S'~:3 • '3',5 .5',6 .5',6 .5'H .5'32 .5'B • 5',:3 .sn .5'N • 5'3'3 .5',7 .5',6 .5'36 .5',6 .5',9 .600 .5';"3 .600

5'~''" • 60:3 • 6.a4 .60:3 .6~7 .6Ht .~~7 .61):3 .6\)4 .6~~ .6035 .Oel .607 .610 .60:3 .6,)', .60'? .605 .601 • .5'~·~ • '3',:3 .6).)0 .600 .600 .5'?'? .000 .600 .601 • -:'1)1-) .600 .5',8 .5'?5 • .5',2

BAS

.'586

.58',

.'590

.59:3

.594

.S'?5 s,~"

• '5'?2 .S'H .5';11 .S'H .5'?5 .5'N · '5'?5 .5',4 .593 .S'H .595 . 5',4 .5'N .59:3 .5',::; .592 .5'?S .5',5 .5',4 .5',1 S'~"

HAUT

* PRISES DOUBlES

.'3n • '3'?5 .6010

5'::'" ..... • ~'14 .5',2

* PRISES LAT. GAUCHES.

• '3'?'3 .595 .602 .600 .601 .6as .59:3 .6-)0 .59'3

.5'3::;

.5"S

.'3'31 • '3'?4 • 5';1,;5 .'5':3 .5'?5 .5'?:3 .5'?2 .5'?'5 • '5'?'5 .5'?7

* PRISES lAT. DROITES.

7";' 7'3 76

.5'?4

.5',2

.5',4

.5'32 • '5'?4

• 5'?:3 .5'32 • 5'? 1

MACH

HUB. AMONT

:3 "

1 ~) 11

.5'H

.593

.594

.5'H

.'3'?:3

.53:3

.5n

.593

.59:3 • '39:3 .594

HUB. AIiAl

2 :3 4 5 6 ('

8 ';'

10 11

.5',',

.599

.59:3

.598

.5',8

.598

.'39'?

.600

.s','?

.597

.596

· 5',1 • ·5·~6 .601 .605 .602 .0;;0:3 .615 .615 .611 .60', .609 .614 • 60:~ .6-)1

• '3"2 .5'?2 .5'3a • 5';'0 .'3'?1 • 5'~2 .'391 • ·5',100) .'3',1 .5'32

* HUB. GAUCHE 5'~"

• '5:3', • '393 .5n .5'34 .5'34 • ,'596 .'5','5 .594 . "!o

.5n • 5'32 .sn .592 .5',1 5'~'

.5',1 • ·5','3 .5',4 .S'?6 .596 .5% .'594 • .592 .'S'34 • ,'S',6 .5'36 .5',6 .S'?7

5'~'::' ..,

• 61)~1 • '3'?6 .61)0 • '3',:3 .5"1

• t55'~ .60' 1

• :364 1.021

• ,S'~·S • 5'~4 .592 • 5'~2 • ,:,,1 .5'?4 .5';''5 • 5'?3 , 5'?6 .5'?5

1. ')5'~ .?0~ • ,";''5 • .:;? 1 • '::,3~

:~ ';'

la 11 12 13 14 15 1:; 17' 1 :3 1''" 2()

21

.6a2

.S.aZ

.61)2

.598

.5',7

.5"'?

.6032

.604

.-505

.61)4

.602

.-51)1

.61)1

.6".J0

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B~$ HAUT s~s * ~l~CH

• • 594 * PRISES DOUBLES * HUB. A~10NT

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" * PRISES LAT. DROITES*

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'+ HUB. 1~~IJCIiE

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HAUT

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• :321 • :321 • :31'; • :318 • :31)" • :3~7 • :312 • :318 • :3'J'~ • :38S • :384 • :31J2 • :313 1 • :31) 1 • :3~J2 • :38 1 • '3~8 , (,?,~

BAS

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HAUT MACH

* PRISES DOUBLES .,. HUB. Ar'10tlT

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• ';':31 , '?51 • '?2:3 , ~03 • :345 • '?~5

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HAUT

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• :300 .• 7';';'

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BAS

.801

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t'lACH

HUB. MMO~lT

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HUB. A'· ... AL

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* PRISES L~T. DROITES*

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· :~ 1'3 .%:'3 · '312 • :~ 1·3

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1. 142

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t'IACH ..

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* PRISES DOUBLE3 • HUB. At'10tH

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NASA TECHNICAL MEMORANDUM NASA TM-88442 r ' /..) <7 J /J .1/. /V {; it: -. / 2 "{I' ( -1 i

AO~\PTAT'\O"~ TESTS WITH THREE-DIMENSIONAL ABJtJ5TMEN'l'S IN THE RECTANGULAR

WORKING SECTION OF THE FRENCH T2 WIN~~t~NNEL, WITH A. 'T1Pr: AS 07~ SWEPT -... WING,AMODEL I"'~TAL..L..E'O


Translation of "Essais 'd'adaptation tridimensionnelle' de la veine rectangulaire de la soufflerie T2, en presence d'une maquette d'aile en f1eche du type AS 07," Rapport Technique OA 34/3075 (DERAT 12/5015 DN), O.N.E.R.A., Centre d'Etudes et de Recherches de Toulouse, November 1985, pp. 1-24 (plus figures).

N86-28964· # National Aeronautics and Space Administration. Washington. D.C. TESTS WITH THREE-DIMENSIONAL A[)JUSTMENTS IN THE RECTANGUu\R WORKING SECTION OF THE FRENCH T2 WIND TUNNEll. WITH AN AS 07-TYPE SWEPT-BACK WING

~ MODEL A. Blanchard, M. J. Payry, and J. F. Brei! Jul. 1986 161 P Trans!. into ENGLISH of "Essais d'Adaptation Tridimensionnelle de la Veine Rectangulaire de la Soufflerie T2 en Presence d'une Maquette d'Aile en Fleche du Type AS 07" rept. OA-34/3075, DERAT-12/S015-DN ON ERA, France, Nov. 1985 p 1-24 Transl. by The Corporate Word, Inc., Pittsburgh, Pa. (Contract NASw-4006) (NASA· TM-88442; NAS 1.15:88442; OA-34/3075; DERAT-12/S01S-DN) Avail: NTIS HC A08/MF A01 CSCL 14B

gn text until

The results obtained on the AS 07 wing and the working section walls for three types of configurations are reported. The ....... ..I"C..-"'""-

first, called non-adapted, corresponds to thf~ divergent upper and lower rectilinear walls which compensate for limit layer thickening. It can serve as a basis for complete flow calculations. The second configuration corresponds to wall shapes determined from calculations which tend to minimize interference at the level of the fuselage. Finally, the third configuration, called two-dimensional adaptation, uses the standard method for T2 profile tests. This case was tested to determine the influ~nce of wall shape and error magnitude. These results are not sufficient to validate the three-dimensional adaptation; they must be coordinated with calculations or with unlimited atmosphere tests. Author

to{ ~b NISTRATION 1'{~

JULY 1986 1£ Experimental nr _ Step~ NASA Langley

5 Br~t~ :~~665-5225, USA. Center, Hampton,

l ~~ .. --. --------'-----'

NASA TECHNICAL MEMORANDUM NASA TM-88442

/V 2 10 -, ;;~ 2 C; (I' 1/ 4( AOAPTAT\O,.!>

TESTS WITH THREE-DIMENSIONAL Af)JtJ5TMEN~ IN THE RECTANGULAR WORKING SECTION OF THE FRENCH T2 WIND T~NNEL, WITH Aa

I~"'''' T1P~ AS 07~ SWEPTiAMI!iC WINGAM DEL IrJ£TA'-\"£C


Translation of "Essais 'd'adaptation tridimensionnelle' de la veine rectangulaire de la soufflerie T2, en presence d'une maquette d'aile en fleche du type AS 07," Rapport Technique OA 34/3075 (DERAT 12/5015 DN), O.N.E.R.A., Centre d'Etudes et de Recherches de Toulouse, November 1985, pp. 1-24 (plus figures).

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• 19n text until p"ease reference lore

further notice:

.~

NATIONAL AERONAu'!'J.CS AND SP WASHINGTON, DC 20546

E ADMINISTRATION ~f~6 JULY 1986 If Experimental

E S~~oS1~ ~ASA Langley r. tOP 2, 25 USA

'ques Branch, a1 n VA 23665·,52, ' iechn1 h Center, HamptO ,

p.esearc

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PIi! 6 f' •• I •• "';n~ O.~.n;.c>';c>n Coc!. THE FREf:J~!:k T2 WIND TUNNEL WITH: O'IAS' 07~ SWEPT- ' ~ WIN~"MQDET. 1",~~Ay.....E" 0,

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National Aeronautics and Space washingt:on, DC 20546

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Translation

Administration

l~. Supp·',",.n'o,,, 1'10'.1 Translation of "Essais 'd'adaptation tridimensionnelle' de la veine rectangulaire de 1a soufflerie T2, en presence d'une maquette d'aile en fleche du type AS 07," Rapport Technique OA 34/3075 (DJ;:RAT 12/5015 DN), O. N. E. R. A., Centre d' Etudes E!t de Recherches de Toulouse, November 1985, pp, 1-24 (plus figures).

- t.' / £;:{t-~~l 1 tl. A~.ltoc' This report pre ents the resy'l ts obtained on the AS 07 w4-Rg and the • working section walls fo~ three typespf configurations.' The first,~~tt.ed 11~~~ "non-adapted,'!!~~iresponds to ~ divergent upper and lower ~ctili~~Jalls b~)I\

. which compensate for ~~ayer t\\"fc-i.~~H1g •. It can serve as a basis fO'r ~=---, .... \~'A< r- .pletoe .. flow calculations. The second configuration corresponds to wall shap~s

o determined from calculation's which tend to minimize· interference at the level of the fuse;Lage. Finally., the third 9?:nf~~ calle~ "two-dimensional adap.ta-tion! II uses the st~mdard 1!lr.th~d, for~_ ~ests, This case was tested to determine the influence 0 ~waIl'i:ha a ana-error magnitudeS. These ~esults are' not sufficient to valida 'the th e-dimensional adaptation; they must be coor-

dinated :with ca1CU~~iQ s o~ Wij~~J~es.ts. "

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TABI~E OF CONTENTS

NOTATION

1 - INTRODUCTION

2 - ADAPTATION PRINCIPLE 2.1 Two-dimensional adaptation

2.2 'I'hree-dimensional adaptation

3 - EXPERIMENT EQUIPMENT 3.1 Working section equipment

3.2 Mounting the wing ~ 3.3 Acquisition and &XemiRatlonrprogram~

~~~J 4 .. SUMM}~RY OF TESTS MADE

5 - CONTROL TES~ (4 ~ JLw ~ 5.1 ~ by wall rotation

5.2 ~n"\convergence. 5.2.1 Three-dimensional adaptation


5.3 Non /2.0/3.0 comparison

5.4 Visualizations


7 - CONCLUSION

REFERENCES

LIST OF FIGURES

ANNEX 1 - Cz

2 - Kp

3 File listing

Rages

4

5

7

8

8

9

9

10

11

13

17 17

17

17

18

18

20

21

22

24

25

tI

3

~~~--~~-------------.------------

NOTATION

~:) Cartesian coordinates in the reference working section zp (porthole axis)

: X} Cartesian coordinates in the wing reference (leading

edge to socket)

C Profile chord of the wing section considered

Angle of the model (fuselage axis)

-r;J; ~ Mo -I-nfiliiLe Mach~~t~~=tIt--=the· 'l:~

M Local Mach (wing or wall)

Kp • p_po

! p Vo2

2 J. Pressure coefficient

Cz Local or complete-wing lift coefficient ;

= ( Kp. d(cb) J.".!iL

tI

J 0 vI Vi-I)

Ao ~P~,..IC:>"'.s TESTS WITH THREE-DIMENSIONAL ADJUS'PUEN'rS IN THE RECTANGULAR

WORKING SECTION OF THE FRENCH T2 WIND TUNNEL, WITH·Am T-tPr: AS 07~ SWEPT 'BACK WING MODEL 1",~r"'I..\..ED.


1 .. INTRODUCTION

This test series follows a study done in the T2 wind tunnel ..

with the goal of defining a shape for the adaptable walls which

would minimize their influ~ on three-.dimensional objects ~ placed in the center of the~section or fastened on the side~~.

-to k . ..,.et I,'(\~h r".J,,~. -'>--:tll (1 I

The presen~onf~u~a7!f~t~ working section does not:rL~·{V)"O:VICI. allow ob~§ .. shape~ iderrtical to that of the layGC Of~. ~ -.A...:...i... • +-~ d th d . . 1 d 1 . .. . t· 0 GY-r~ eX1S~ aroun a ree~ ~s10na mo e 1n \Hillmlted- ~""~

atmosph~~ (two completely rectllln&ar and parallel lateral . ~ walls, two flexible and bendable upper and lower walls). The

planned solution thus consists of using the two bendable walls to minimize the influence of the walls on the model.

The method implemented uses solutions developed by "E.

Wedemeyer and L. Lamarche~r~A first series of tests was

done in cooperation with the~University of Berlin on various

existing models [6]:

- a CS revolv.ing body 166 mm long, 0.3% blockage;

- a civil F4 airplane model with l20-mm wingspan and three-

component balance;

- a duck-type military airplane model with the same balance.

Another series of tests was then done on a bigger model £7]:

- a CS body 400 rnm long, 1.8% blockage. tI

*Numbers in the margin indicate pagination in the foreign text.

5

The rE!sul ts and calculations were compared.

The calculation methq9 was optimized for re'~l!tin9 bodies ~ ~ \.c.~~; j-placed in the center of the~section, an extrapolation was tried which placed a half-wing at the wall. In this case, calculati()n~ -i-s- done as if the section were twice its actual width, using the

Mach distribution at the wall measured near the plane of

symmetry.

The results obtained on the "16/1000-scale" AS 07 are

discussed in this report. They can be divided into two groups:

control tests and systematic tests. fL" :;tt. Included in the first group is control of wing anglil~ by

rotating t:he walls. The ~ of the jacks would not permi~e~;J1.1 tJ displacements ~<Lhr calculat~ for ang'; fig eft@ model Q" 'I

cI \\

+2-, we thus used this artificial method after AaviRg verif~~~

its validity.

The three-dimensional adaptation method supplies the WI"\

optimCiiA: shape of the walls from the first calculation, whatevEH the initial position of the walls, this was verified in /8

several test configurations. Finally, an adaptation called 2-D

"~dimensional" was tested; it uses the normal method for ~ 2.0

prefiW-t.ests. This case, without theoretical justification, . ~ "-....,CoI,)

w~fdied "'£'0 ~h:r~blPee~ceof the sa ape ef the wall,),.and the ~.e eftrro~~

The second part of this study corresponds to systematic tests: four configurations were chosen w~ich gave different lift coefficients, without making highly supersonic zones appear on the profiles. For each configuration, three wall positions welre tested:

- The first, called "unadapted," corresponds to the upper and lower divergent ~eeilift8a€ walls compensating for

6

\ .. ''''.''C~ "'"I ~,.

~1)l~~'--~r bO'~

thickening of the 14~ layers; it served as our basis

for beginning three-dimensional adaptation calculations. These particularly simple limit conditions can also be

used for complete calculation of the flow in the working

section.

- The second adaptation

positioned

wall shape comes. from the t~-dimensional

calculationJ the flexible sheets are before the ~_~ ~ ~,

~1'--

- Finally, the last case corresponds to "two-di~ensional .

adaptation"; the iterative process converges ~ a single

C}U+t.. b.-l "'-. /j,{L";-"v'·

~~ For each type of test, three 9tl8t~are necessary to obtain

readings from the six rows of pressure recorders spread along

the AS 07 wing.

The experimental results gathered during this series are not sufficient to validate the three-dimensional adaptation

method used. Additional calculations ~st be made to estimate residual corrections. In these tests,' Ii "- n~eJ::;l influence of

the walls is observed for low lift values or low Mach number

inversely, for 2 degrees of incidence or for Mach 0.8, the iSiI~~~II~~ become significant and can in part be interpreted as variations

in aerodynamic incidence.

2 - ADAP'I'ATION PRINCIPLE

._~_E-~~o purpose of the adaptable walls is to create an ~~~flow around a model, in a working section with finite

dimensionsJ this can be done by controlling the wall conditions, either by their shape in the case of solid walls or by flows of

mass through porous walls. The first solution has been chosen

at T2,~e flexible sheets moved by jacks form the upper and

lower ~of the working section [3).

7

~---~-___ -"-------·------------_.L In the case of a three-dimensional body, it is necessary to

bend ~ w.111s. lo;.a~ed a~.':'~\;-~';...-\,m~ob~el to arrive at a shape ~ ~ Ml':r I;;'f zhr1-~eXiSting around the model in\»I'I~Uoed4

~~~~~~~e~E~ This solution is not at present possible .£ T2, but

on the other hand it is possible to use the two flexible /9

/. j . ' '.~

walls to minimize residual corrections due to the influence of

the walls on the object~.


The details of the process will be found in [2] and

(4); it uses a coupling between the real ~16w in the working l~,,:,\''''''''!.~

section (internal field) and a calculated vir~ua~flow outside

the wind tunnel (external field). Coupling occurs on a control

surface near the walls through speed vector components.

Adaptation is achieved by an iterative ~:~a~ing on the shape of the walls: the components of ~a ~ the control

surfac~come,available at each iteration; they are

extrapolated from the pressure measurements at the wall. The velocities needed on the control surface to achieve an unlimited

external flow are calculated by the Green function following an inverse method. A method of optimized relaxation·between the

internal and external flows for the vertical velocity component,

followed by an integration along each fleJcible wall, supplies

the !!'lew shape of the wall. The real shape needed is obtained by

adding the thic;kness displacement of the four wall limit layers.

2.2 ~hree-dimensional adaptation

For three-dimension~tion, .the process is different [5J: it uses ~ of the model through b~ ~ distr ibution of sourc~ vortices i~W hor~eshoe)

Plac~th~ection ~i This s~atiaat10n ~iv:& a good ;;Urea.entat~~of ,axisymmet :ical bodies mounted in the middle of the working section.

- ) 13 r, ('J,~\' ;.'1 -t/l"l

8

The originality of the method lies in then doing a

linear trclnsformation, which permits passing directly from distribution of velocities at the walls to the adapted form without needing to determine the intensity of singularities. The optimized shape of the walls is thus theoretically obtained from the first calculation; this shape, which is not exactly

"adapted," minimizes residual corrections on the model caused by

the influence of the walls.

1: Using this met;hod ~f-wing at the wall.is "!J';'! ~, because the ~m ~iliati;;t·does not r~~t""2.a wingspan~~~~s nonetheless been tried here by replacing ehe ~

lateral ~~ by a plane of symmetry leading -to a fieti6"al~~ double section width, and t.aking the Mach distribution of the ;Jr..i..:/;'.

c'IDl{<l..-'

flexible walls near the plane of symmetry as reference.

3 - EXPERIMENTAL EQUIPMENT

u- be. J. The T2 transonic wind tunnel is pressuriz~ and can

function at low temperaturE~s; only minimum-pressure and ambient

temperature tests wer~!:Q~during this series.

3.1 Working section ~uipment

The working section has an almost square section of 0.39 x 0 .. 31 ~2 at the entrance. Flexible sheets of Invar

make up the upper and lower walls, equipped with three rows of

pressure recorders whose coordinates are given in figures 1 and

8. The s~llt-pOSi tioning mechanism is descr ibed in [2], [3],

and [4]. <gt!;~delV}A I

:i:ixi

The left lateral ~ has three portholes with pressure recorders placed along horizontal and vertical lines whose coordinates are shown in Figures 7 and 9.

9

The pressure rec()rders are linked to bite Scanivalves,

each Of~~~ can obsE~rve 48 positions in 5 seconds.

The position of the wing in the working section is

given in figure 6. 1~~'o(1t;

;~C~ The Mach number ()f the flow is set by a seeef'ld -~ controllE~d by the computer which controls the ~. ~ ~ .

No other equipment or wind tunnel measurement meth()d ~

we-s used ..

3.2 Mounting the wing

k..t~-The AS 07 wing.\model with a scale of "16/1000" is

shown by the photographs in figure 5. The method of mountin~J the wing on the wall is shown (figure 6), the plane of the wing

and its specifications I\~fe y.iven .(fi~~a~, and the shape of the profilet:~~ it.,and the positions of the pressure recorders are indicated (figures 12 and 13).

cd- cG'1 tW ",Y ~~vLV ,"-.lC h-c.<>U"." M.9. ,1.. ~'Y')

There are six rows, each with 16 recor~ers on the inner and outer sections and one on the leading edge; they are

placed across the wingspan so as to form lines with constant chord percentages. These recorders communicate with tubes placed in grooves along the wingspan; each tube communicates

with three recorders (either on the external wing or on the internal wing). When one of the three rows of recorders is used

to measure pressure, the other two are covered with thin (0.05-mm) adhesive strips. It is thus possible to simultaneously measure pressure on two sections of the wing (one internal and one external); measurement of velocities over the entire wing thus requires three different gysts.~ ~~

porthole, The wing is mounted on a half-fuselage linked to a n rotat~ 4:8L;~aR91iA9 ~ll~g-

/t"tat't.4 ~+~ i.-/ 10

fuselage assembly; on the back of the

the angular reference is the r~~a. part

fuselage [1).

3.3 Acquisition an'2~l2rOgram. The T2 wind tunnel is linked to a _t~_~-D~f,_two W =

computers, one concerned wi.th creating and ~ the g.y.s..t

and the other with obta~g_data and storing measurements to

disk at the end of w.e ~~ ~. ~

These tests are Purs~antLto the series done on the /11

C5 body and use its principal elements.

Disk cart:ridge LU 26, Program LU 34, Test files, calculation files

Acquisition program

(TEACQ)

(RAFAL)L PARC 5

or

PARC S

(lance ACQC5)

(uses PROJ and ADAP.)

Fixed walls:

No adaptati~n ~

during ~:~ ~

Two-dimensional . adaptation

Ini tialization of programs {With (TR,) RINC 5 (For PARC 5)

or (TR,) RINC S (For PARC S)

Test file

AD ,--- test number from AD 100 to AD 173

11

II

wall positioning 'file -- any test file - or calculation file _ or"special file AD 4:

AD 444:

AD 445:

AD---

AD 9 ---Divergent t:e;~a~ walls;

symmetrical ~ayers. ~

AD 4 + 10'~rotation upward 04(.~ •

AD 4 + 30' ~rotatlon upward

Three-dimensional adaptation calculation

Calculation from a test file AD ---

VKJ 43 Calculation of wall shapes without rotation

VKI M Calculation of wall shapes with rotation

! LJ)

I ?l:::=---

.... --- - ---- - - - --. 780 "''''

---tFiling to disk I

.. I I

: ~& 310 mlft

. ,

!1le for new calculated wall shapes

- section length 780 mm

- ratio c = hlb = 2.1081

- reference recorders:

right lateral RL

- weighting coefficients

file VKJ - R (cartridge

LU 43)

AD 9 --- beginning test number for the calculation

E!0gram~; for examination ()f AD--- files

L'l'CS:

- graphs local profile Mach numbers

- graphs Kp - lists AD file

- calculates Cz 12

LTC 51: - graphs wall Mach numbers - graphs wall shapes

starts LTC 52 (does eln RP, LTC 52)

LTC VK: - graphs only wall shapes calculated by VKI 43 or VKIM

( from AD 9 - - -) •.

- SUMMARY OF TESTS PERFORMED

A previous study was done on the AS 07 wing (1]. We

erified in one case that the same results would occur, althou9h~ o. (j he working section was modified when the T2 wind tunnel was ~

fOlr cryogenics.

The first control tests were done by measuring rows 2 and 5 pressure recorders for the Mach numbers and incidences

cHeated below:

-~ 0,7 0.8 )

) - )

+2° X X X )

0 X X X ) _2° X X )

-)

13

Four configurations were selected for systematic tests: L!l

-)

0,6 0.7 0,8) )

(----=*--~---:---:) (+2° X: : ) ( ::) --- ------- ---- ---) ( :: (0° X: : X )

(------- -------:-------:-------» ( . :: (-2° X ) ( )

'ltL.u') ~ v6.{JL4-)

hey correspond to a sampling of lift coefficients and ~ ofi~e Mach e£fe~£ee~, while limiting the supersonic ones which appear on the profiles.

Figure 1 shows the list of tests in chronological order,

nd figures 2, 3, and 4 classify them by configuration.

We first Sho~:.~~r~~:ijln~~e uppe~_~I!.i ~ower walls as equivalent tO~Athe m;Jel at 1[he sam~~. This~~O.--.--~ ~~ was made necessary because the ~of the jacks did VV~

-&,-o.""uv . t permit the displacements required by calculation of

ree-dimensional adaptation for a model incidence of +2".

- DivE~rgent ~QtiliRQa~ walls I

·Mo ( )

0( , ( 0( " •• 1.1 0,6 0,8 ) 6tllotd .• ( 0\$ a.: ·-s.tw l

( )

+2° ( +2° AD4 AD 120 : . ) ( +1,5° AD 445 AD 122 ) ( ----- _.- ------) ( )

O· ( 0° AD4 AD 107 - AD 109 AD 108 - AD 132 ) ( -0,5 0 AD 445 AD 137 AD 139 ) ( )

14

- !!!!.ee-dimensional ada.E..ted walls

Mo

( ) (0( CALCUL 0.6 0.8 )

Q( afrod. • O· ) )

(:---, ( ( O· VKI 43 117 AD 119 ) ( -0.5- VKI M 138 AD 141 )

(,------------~~-----.~-----------)

The three-dimensional adaptation method theoretically

supplies the opti~ shape of the walls from the first

calculati(m~~atever the initial position of the flexible

~. C~ls were done in this respect for the following

configurations:

Mo ( )' ( 0(, 0.7 0.8) ( ~~pl .. " ) ( ) ( +1.5· AD 127 (I) ) ( AD 128 (2) ) ( : AD 129 (3) ) (------ -------:--------) ( :) ( 0° AD 115 (l) : AD 118 (I) ) ( AD 116 (2) AD J 19 (2) ')

( -- -------: ----) ( ) ( -0.5· Al) 140 (I) ) ( Al) 141 (2) ) ( : ' )

e figure in parentheses after the file number indicates the rder of the iterationJ the wall-positioning file thus results

calculation of the preceding test. (Iteration (0) is the

est don~! with Jr~f~~~e5.walls.)

We also verified that the tests called "two-dimensional aptation" converged rapidly, as is the case for the prcfile 2D

ests; it is sufficient 1&F-:::tOQ:a:t to compare the wall position~ of

15

---..... ----......... ~-------.. -

the 3rd the same ~; the two

positions are always close. In general, the beginning shape chosen is near the adapted shape, but we have tested this

convergence in the two particular cases when the beginning shape

was far from the adapted shape. cl ~ b~'i.. f~ Ch!_e~s \ .... L.A

AD 4: ~~f!.iw.:rwalls diVerge~~'·d·' __ J.;;-s,~ptf, .. :9v ~. C.J-tk.;

~ Lt m~. " M-J~1'\A-y,jj;UL-CrJJI.~,,: t L -C <> ud". ~ /15

Configuration: Mo = 0.7 ~ = +1.5-

Configuration: Mo = 0.8 « = o· File AD 130 (1)

File AD 133 (1) followed by File AD 134 (2)

Comparisons were made between the various wall positions;

hey are noted:

sb~l4 - "Non," for divergent J~ctlliftear walls

- "2D," for two-dimensional adaptation done with the PARes program

- "3d," for positioning of the walls in the shape

calculated by the VKI 43 or VKI M program

It was decided to do systematic tests for the three cases

f "adaptation," the non-adapted case serving as a basis for

hree-dimensio~al calculation (any wall shape will work), this

ase can also ~erve as a basis for complete flow calculations,

ecause her.e the limit conditif~e particularly simple. The

wo··dimensional adaptation, ~;;;S~ the subject of the

tudy, was systematically tested to use as a comparison with the """"" ssumed optimai shape.

Finally, four configurations for three cases of adaptation,

~produced three times to h~~~ocity field on all of the lng, were tested; these 36 ~~make up the systematic tests isted in figure 26a.

16

5 - CONTROL TESTS

We will not present all the tests done, but only a selection of cases judged most interesting, since the goal of

this series ~not to evaluate the AS 07 wing. /' L_ _ 0 ,0 A () (' h \ n" ~. ,D i' , ) rn . '7 r" ~r~,-. ~~. CA/I (( t I('~'L ~ "'''(c, __

5.1 Arflg1in9 by wall rotation '

, ~ Of the five configurations tested (para9raph 4), three

are presented. The first corresponds to Mo = 0.6 and ~ = +2"

for ~trl~~.r walls (figure 14); this is the configuration

which obliged us to use this~e:, as the three-dimensional

case could not be tested.

Figure 15 shows the comparison of Mach numbers on the

walls and on the wing, for an aerodynamic incidence equal to O' and a Mach number equal to 0.8, in the case of £eetiliRear6f~~ walls. Figure 16 presents the same configurations but for wall

'¢D . shapes c:oming respectively from~calculatlons VKI 43 and VKI M.

;S :J) aaLl P :1:: o---~'/

The results of figures 14 and 15 sho~hat the high ~~~:~~ ~ ----. Mach case is the most , but the.!Cor=. dence'-of the

tests remains good. Figure 16 ,shows that the VKI M calculation o...c....o

makes perfect allowance for ~otal rotation. ,

i ~~. It· is thus possible to display a model incidence ill

different from that desired and to compensate by rotating the walls.


~veral calculations for optimization of wall Shape wereJ;oRReetedlfor one configuration. The last test is

always recalculated, leading to a wall shape which by definition

17

ill not be used, but which will in fact constitute an

dditional iteration.

Of the four tested cases, two are presented in

igures 17 and 18, the first (Mo = 0.7 and = 0·) shows that he adapted shape is practically obtained from the first

'terationJ in the second case--much more difficult (Mo= 0.8

nd 0(= +2")--it is necessary to wait for the second. Q ~ -11> alculation. This second case corresponds to a freely ~ U ~6 upersonic regime of the wing which will not be studied

ystematically herein.


In all tests done, the 3rd i ter~~ J! always dentical to the 4th and last iteration of the ~, even when

he upper and lower walls have been prepositioned in a shape ery different from the "adapted" shape. This is the case shown

n figure 19 corresponding to Mo = 0.8 and «= 0·.

To confirm the validity of this statement, a

econd test was done, positioning the flexible ~~ on the~ receping shap~ the values obtained can thus be considered to

orrespond to the 4th, 5th, 6th, and 7th iterations of the test;

hey are all identical (figure 20), which confirms that the

onvergence was lwell obtained.

5.3 ~)n/2-D/3-D comparison

Two cases are presented here, one Qf which is not part f the systematic tests:

Mo = 0.7 - Mo I: 0.8

(){ = 0"

18

The bervea following tt~es of "adaptation"

become more significant as lift aR~~Mach number ~pstt6am increase. The adaptation called "two-iiirnensional" gives results

nearer to the non-adapted case; in fact. everything happens as if the aerodynamic incidence of the two~oimensional case were

igher than that of the tests with~a wt!l shape adapted in three imensions. On the other hand,rre~tIti~e-aFLwalls lead to a

igher effective Mach number upstream ~'blockage effect).

In the first Ca~ffigUre 2U" the ~e moderab~; hey are more significant~n the seconO! case (figure 2~ bservation of the 8~ti~2of the walls leaving the GOAver9~t figure 21) shows that,effectively) the direction of the flow

pstream is no longer horizontal in the "2-D" case, unlike thE~

3-D" case; the angular referen<?e.91as j,i.ven by the "non-adaptE~d" The effect produced is i-neon~e~'a\le7 because we /17

reviously demonstrated that rotation 0,£ the wall~Q!5embly

odified the aerodynamic incidence of the model; ~owever, this

s not sufficient to prove thal, the 2-D case is &~=s, ~~ ecause the direction of the etJ.~~~t~ lines inll"liliittea.~...J. -

~ .£.ti,: UVYt~-., v--'>\ C-t> ;"''\A~ 12 • ... ~~:.w.t~e-T·'5.~not known. We note also the very different shapes 0-'1.1.)

f the walls downstream; they go downward for the n3-0 n cases f

hich is logical allowing for the chosen ~jzat~ ~ orseshoe vortex) and the calculation made (in the plane of

But on~e more, that does not prove that the shape btained is optimum.

r (

Finally, one can observe on the last figure (23) that

e effectJ~liElea b?,Zmodifying the shape of the walls is not:

nstant across the wingspan. This was predictable due to the

rking section geometry itself, allowing for twist of the wing

d for three-dimensional effects.

19

G

tI

5.4 Visualizations ff()-t-v..J

For thr~e configurations, oil~sualizations were done 6~~~f h ' , " h d' on the left 0 t e worklng sectlon, glvlng t e lrection of

~~c:.""'~2. ' 4 f' h d f h ' the e~££e~ llnes 55. mm :rom teen 0 t e wlng. Reference marks were made, making it possible to locate the positions

St ... t."'~ "'2 ' , ." relative to the eurre llr~es and to measure thelr devlatlons.

- Zoo -- . --+. _. --..-. - . .-...... - -.- ._f-.-YI"tUt..,'1~ '!.e(..{ ... C')

fl. .... ..

... ",

The end of the wing is located between the abscissas 91.06 mm and 135.86 mm from the porthole (figure 6) and very

near to the section axis (function of the incidence).

The maximum deviations noticed are located on the~ section axis slightly behind the tip of the wing (figures 24,

25, and 26).1

( Walls dmax ) ( MQ 0( ) ( )

( · ) "Non-adapted": - Figure 24 ( 0,6 +2· "

(5· •••••• 6·) ) ( AD 4 )

(-- ----) ( ) ( 0,6 +2· · (5· •••••• 6·) ) ( 'Adapted 2-D: ) Figlllre 25 · . ( : --) ( -· ) · (

0,6 -2· "Non-adapted": «la,s· ) Figure 26 ( ) ( AD 4 )

20

tI

The photos taken from behind clearly show the L!!! eviations of the ;~;~8A~lines.

_ SYSTEMATIC TESTS

.w~ {or the 36 g.usts,\that lmade up the systematic tests

~t~9';~ 4 and figure 26a), the following information is iven: wall shape (~igures 27 and 28), Mach numbers 6~ the

hree rows of recorders on the adaptable walls lfig~res 29, 30, .s,~ ,

1, and 32), Mach numbers of the left lateral ~ (flgures 33,

4, 35, and 36) following the horizontal axis or the three erticals, and finally spread of Kp on the AS 07 wing (figures

7 to 44).

Numerical values for these curves are given in the attached

est listings. File numbers corresponding in chronological

rder to the experiments were kept in the interests of clarity.

Here will be found a systematic comparison' of the three

of adaptation--"Non/2-D/3-0"--and their influence on the .~~ , t 'b t' ~ , , I h ' t~~ , lS rl u 10nS,WHose pr1nclpa c aracterlS ibs~were seen 1n

5.3.

Finally, .integration of Kp for each section supplies local , coefficiJnt Cz. The values are tabulated in figure 45, were traced along the wingspan of the various

nfigurations tested (figures 46 and 47). It is observed that

e internal wing changes less rapidly than the external wing

ith incidence (figure 46) O~Ch number Upstream (figure 47).

On the other hand, the~tween the ·non-adapted· and adapted 3-D" cases increases with the lift.

21

"

Local Cz)were multiplied by the chord of the profile in the

ection considered; the product Cz • C represents local /19

ontribution to wing lift. The values obtained were traced in his representation (figures 48 and 49); this weighting modifies he appearance of the curves ("elliptic" distribution plane),

ut the observed tendencies are the same.

Finally, integration of the curves in this last

epresentati~n supplies the overall lift coefficient of the

ing, which m reported as a function of incidence (figure

0). We have also re~he lift measllred during the S~c-o..>..o.,I-t

reeed ing ser ies [1], between reetllrn9ar walls for a Mach umber upstream of 0.47. The effect of compressibility is felt

ore as supersonic zones develop on the wing.

- CONCLUSION

~ This series of tests on the AS 07 wing is ~ as a

tudy on three-dimensional adaptation of the T2 wind tunnel. It ses the two flexible walls to minimize residual corrections in

he presence of a three-dimE!nsional model. ~It implements the l'-e~e~C:>'I,.-h..-bo""2

• Wedemeyer and L. Lamarche" method where 9mati2atie~ of he model by a distribution of singularities adequately

epresents an aXiSymmetrical~. Extr~~~~ these

thods in the ;case of a half-~~e~~has no ultimate all it serve~ merely as a preliminary phase, to observe the fluence of wall shape tn various sections of the wing, to

udy the convergence of the method, and to make adjustments

otation of walls, incidence, etc.).

On the other hand, these experiments can serve as a basis r calculating potential three-dimensional flow around the

del. Then, a three-dimensional ebjeot placed in th~ection ~

22

tI

ould be more it would lead to

evelopment, as for axisymmE!trical bodies, of a method of

daptation minimizing the influence of the walls on the model.

At present, it is difficult to know if the shape called Q ~ Ie ~ adapted 3-D" is nearer to the values of unlimited atm9sphere~~ han the shape "adapted 2-Dv" but it is definitely not the ptimum shape. /f,,'V/I\ ... flC)U

I ,

~ Jt J6~( tests will ~~ ~ direc~al ~t).layer

"_e-a4:1+f~2cm the lateral k'lall at the level o,f the ~ the

ingtr. The! direction of the c:lA-~~~'f2Iines in this area will bE! n important element in the E'.eality-calculation comparison~

23

R1~FERENCES

A. Mignosi, A. Seraudie. "Etude d'une maquette d'aile en fleche a la soufflerie T2 de l'ONERA-CERT [Study of a swept-back wing model in the ONERA-CERT's T2 wind tunnel]." DERAT technical note No. 13/5006 DN, March 1977.

J. P. Archambaud, J. P. Cheva11ier. "Utilisation de parois adaptables pour le~tsjajs en F~~~~nt plan [Use of adapt.&.~·~ walls for tests in p.Ta~~lfii"Mrr:- ONERA TP No. 1982-38, AC;:p\I't> ,P-"33S-

}~ AGARD/FOP meeting in London, May 19-20, 1982.

J. p~~~c~ambaud, A. Seraudie •. "Etudes de parois adaptables a T2 ~AClapt:ab1e wall ~~ T2) ." ONERA TP NO. 1983-150, 20th AAAF Colloquium, Toulouse, November 8-10, 1983.

J. P. Cheva11ier, A. Mignosi, J. P. Archambaud, A. " ) Seraudie. "Adaptable walls il:1_~ T2 \.~ind tunnelAQ*'IPT',vG; WA~- ~!>I~ Pril:1~plec, execution, and som~E»Ea~ ~ of two dimensieA&l r~urts.n La Recherche Aerospatiale, 1983-4, ~p. 217=21£.

L. Lamarche, E. Wedemeyer. "Minimization of wall interference for three-dimensional models with two-dimensional wall adaptation." V.K.I. Technical note 149, Rhode Saint Genese, Belgium, March 1984.

6. J. Po Archambaud, J. B. Dor, A. Mignosi, L. Lamarche. Premiers essais d'adaptation des parois auto-adaptables bidemsionnelles de la s£u flerie T2 au~our ~'QQsta~le§.l~ tr idimensionnels [~: · I \. ;atd 0 t test'~ of;t~menslional self-adapting walts ~ ~h~ ~wind tunnel around threedimensional e~~cies]~ ~~A Technical Report "No. 33/3075

, September 1985.

7. J. P. Archambaud, J. B .. Dor, M. J. Payry. Rapport sur la deuxieme campagne du CS [Report on the second C5 series]. (To be pu!blished soon.)

24

tI

LIs~r OF FIGURES

1. Test tables u -

- List of tests - Rows of recorders 1-4 - RowS of recorders 2-5


1 2 3 4

2. ~ount~ng the wing in the section

- Presentation of mounting 5 - Drawing of wing mounting 6 - Drawing of pressure recorders on walls 7 - Pressure recorder specifications - flexible walls 8 - Pressure recorder specifications - lateral portholes 9 - Plane of the wing 10

Dimensions of the wing 11 - Profiles 12

Specifications of wing pressure recorders 13

Control tests

3.1 Rotation

- First control (el = +2·, Mo Wall shape Wall Mach No }1lO-C--Q\ f'\..O

Prof ile Mach 'I'lc>

- Second control (0(. = 0·, Mo Wall shape Wall. Mach ""0

Prof ile Mach ~

= 0.6 Non-adaPt~)

= 0.8 Non-adaPt~)

- Third control (0(= 0·, Mo = 0.8 3-D) Wall sha~e Wall Mach ~ Profile Mach '"'0

3.~A~ergence ~~s A _:;,,;;,.:.:.:..;::.::..;_;z..::.::..:..=.=--==~-==..:

a - 3'-D

- First case (cx= 0·, Mo = 0.7) Wall shape Prof i le Mach N:>.

- Second case (ol= +2·, Mo = 0.8) Wall shape Prof ile Mach "'0

14

15

16

17

18

25

b - 2··D (0(. =0·, Mo = 0.8)

_ Beginning of AD 4 (File AD 133) wall shape Profile Mach -

_ Beginning of a similar shape: AD 133 (File AD 134) Wall shape

19

Profile Mach ~ 20

3.3 ~on/2-D/3-D compari~

( 0<. ::: o· , Mo = 0.7) Wall shape Wall Mach ~

(0< ::: O· , Mo = 0.7) Profile Mach t..(2) Profile Mach~~3)

(0(. == 0·, Mo = 0.8) Wall shape Wall Machn..o

(0< == O· , Mo = 0.8) Profile Machllo(2) Profile Mach 1\0 ( 3)

- (ex == O· , Mo = 0.8) Kp

Visualization, left lateral ~ ~\Qt..J1. - «()I. =: +2· , Mo = 0.6) Non - front

Visu (2) - back

- (ex :: +2· , Mo = 0.6) 2-D - front Visu ( 1) - back

- (C< :: +2·, Mo = 0.6) Ncm - front Visu (3) - back

Use in 4 base cases j

5.1 Wall ~haEe -c..l = -2· Mo = 0.6 -0' = +2· Mo = 0.6

-c:( = O· Mo = 0.6 -0( = O· Mo = 0.8

5.2 ~daEtable wall Mach ~o

- (0<.,:: -2· Mo = 0.6) - Non - 2-D

3-D

'YflctC)\ 'n,(J( 21

21

22

22

23

24

25

26

27

28

29

26

(~ ~: o· Mo = 0.6) - Non - - 2-D - 3-D 30

- (0(. :: +2· Mo = 0.6) - Non - 2-D - 3-D 31

- ("" :::: o· Mo = 0.8) - Non - 2-D

S;~f. - 3-D 32

5.3 I.atera1 },wa11 Mach~ - . - (~ :: -2· Mo = 0.6) - Non

- 2-D - 3-D 33

- (ot :: o· Mo = 0.6) - Non .. 2-D •. 3-D 34

- (0( := +2· Mo = 0.6) .. Non .. 2-D .. 3-D .35

- (0{= o· Mo = 0.8) .. Non .. 2-D .. 3-D 36

5.4 !£ J - (of. = -2" Mo = 0.6) Non adaptahl.e 37

- (0( = -2· Mo = 0.6) - Non - 2-D - 3-D J

38

- (0( = O· .. Mo = 0.6) Non adapt~ 39 I

- (0( = O· Mo = 0.6) - Non - 2-D - 3-D

~ 40

- (-.\ = +2· Mo = 0.6) Non adapt~ 41

- (~= +2· Mo = 0.6) - Non - 2-D - 3-D

~ 42

- (0(.= O· Mo = 0.8) Non adaptabTe 43 tI

27

5.5

- Cz - Cz - Cz - Cz - Cz - Cz

Cz .-

Mo = 0.8) .. Non 2-D

.• 3-D

rreeap ittll.ti :e ~"'M""''''I'-~ Mo = 0.6 (3 1nc.) oC = o· (2 Mac hI f\.o.;Y -ru-V

X chord Mo = 0.6 (3 inc.) X chord 0<. = O· (2 Machl~) (oe.)

44

45 46 47 48 49 50

28

tI

TO :

VIA :

FROM:

D

Dr. Robert A. Kilgore TAD-ETB, M$-287

LaRC/Kaye Lee

NASA HEADQUARTERS NIT~4/ Tim Rowe

r--i '--_. "

Jut 111986' DATE

<jJZl{42.

Per yO_lJr request, the technical translation NASA TM-13~ has been prepared and '-a copy is at1:ached. Please complete the 'blocks and ,~, return this form, after you have read the translation_ If errors are noted, returnoa copy of the translation with your corrections. Your assistance will be appreciated.

A copy of NASA TM- is attached for your information. If you wish f you may completE~ -the blocks below and return this form. Your coop~ration will be appreciated.

TO: : NASA HEADQUARTERS DATE

F'ROM:

scientific & Technical Information Branch Code NIT-4 Washington, DC 20546

NASA TM-

NASw- 4005

A. The Translation

~ o o

Furnished valuable new data or a new approach to research.

Substantiated information available from other sources.

FurfiShed interesting background information.

Other:

3. The Translation Text

c.

o Is / IT Is

technically accurate. _.

satisfactory·v. except for minor deviations.

o Is unsatisfa~t6ry because:

Notes or suggest;ions·: See. ~~ ~

D. Review Campletec:

Tim Rowe

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NASA-TM-88442 (q19:l · 2013-08-30 · nasa technical memorandum nasa tm-88442 tests with three-dimensional adjustments in the rectangular working section of the french t2 wind tunnel,