Copy RIvI L51G31

NACA

RESEARCH MEMORANDUM

SYSTEMATIC TWO-DIMENSIONAL CASCADE TESTS OF

NACA 65-SERIES COMPRESSOR

BLADES AT LOW SPEEDS

By L. Joseph Herrig, James C. Emery, and John R. Erwin

Langley Aeronautical Laboratory Langley Field, Va.

ENGINEERING DEPT. LIBRARY AIRCRAFT

SSFtCAT0N CHANGED DALLAS, TEXAS

AUTHORII(

onni Gotetae of the United States within the meaning of the Espionage Act USC 50.31 and 3. talon or the revelation of its contents in any manner to an unauthorized person is prohibited

Information so classified may be Impart suns in the military and naval services of the United States, appropriate civilian officers and tI the Federal Government who have a legitimate Interest

j*F;R* ------------------ 17

thereIn, and to United States CSIner.s a ;siy and dlscretLn abe I necessi t y Oust be Informed thereof.

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

WASHINGTON

September 14, 1951

https://ntrs.nasa.gov/search.jsp?R=19930093730 2020-02-09T00:26:20+00:00Z

NACA RN L51G31NATIONAL ADVISORY COMMITTEE OR AERONAUTICS

RESEARCH MEMORANDUM

SYSTEMATIC TWO-DIMENSIONAL CASCADE TESTS OF

NACA 65-SERIES COMPRESSOR

BLADES AT LOW SPEEDS

By L. Joseph Herrig, James C. Emery, and John R. Erwin

SUMMARY

The performance of NACA 65-series. compressor blade sections in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and, for high-pressure-rise conditions, porous flexible end walls were employed to establish condi-tions closely simulating two-dimensional flow. Blade sections of cambers from C1 of 0 to C1 of 2.7 were tested over the usable

angle-of-attack range for various combinations of inlet angle of 30°, 14.5°, .600, and 70°, and solidity a of 0. 50 , 0. 75, 1.00, 1.25, and 1.50. Design points were chosen on the basis of optimum high-speed operation. A sufficient number of combinations were tested to permit interpolation and extrapolation of the data to all conditions within the usual range of application.

The results of this investigation indicate a continuous variation of blade-section performance as the major cascade parameters, blade camber, inlet angle and solidity were varied over the test range. Summary curves of the results have been prepared to enable compressor designers to select the proper blade camber and angle of attack when the compressor velocity diagram and desired solidity have been determined.

At a few test conditions, an upper limit to the camber that could perform satisfactorily was found. -These results provide information as to the maximum value of the loading parameter, expressed as the product of solidity and section lift coefficient based on the vector mean velocity, that can be used effectively in compressor design. Analysis of the trends indicated that the common practice of employing a constant maximum value of the loading parameter for all inlet angles and solidi-ties fails to define the observed performance of the compressor blades studied in this investigation.

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An index that the positive and negative limits of useful angle-of-attack range occurred when the section drag coefficient reached twice the minimum value was used to estimate the operating range of the com-pressor blade sections studied. A broad operating range for these sec-tions was observed, except for conditions of highest pressure rise across the cascade corresponding to high cambers at high inlet angles. These conditions are not typical of usual design practice and no dif-ficulty should ordinarily be encountered in employing these blade sec-tions. In general, the observed performance of NACA 65-series compres-sor blades in cascade is considered to be very satisfactory.

INTRODUCTION

The design of an axial-flow compressor of high performance involves three-dimensional high-speed flow of compressible viscous gases through successive rows of closely spaced blades.. No adequate theoretical solution for this comlete problem has yet appeaied nor considering the complexity of the problem does it seem likely that com-plete relationships will be established for some time. Various aspects of the problem have been treated theoretically, and the results of those studies are quite useful in design calculations. All such studies, however, have been based on idealized flow, neglecting effects of one or more such physical realities as compressibility, finite blade spacing, and viscosity. Consideration of viscosity effects has been particularly difficult. It appears, therefore, that in spite of advanães in theoretical methods, theory must be supplemented by experi-mental data for some time to come.

Some of the information required can be obtained only by experi-ment in single-stage-and multistage compressors. Much of the inforina-tion, however, can be obtained more easily by isolating the effects of each parameter for detailed measurement. The effects of inlet angle, blade shape, angle of attack and solidity on the turning angle and drag produced can be studied by tests of compressor blades in two-dimensional cascade tunnels. Cascade tests can provide many basic data concerning the performance of compressors under widely varying conditions of opera-tion with relative ease, rapidity, and low cost. A number of successful high-speed axial-flow compressors have been designed using low-speed cascade data directly. A more refined procedure, however, would use cascade data, not as the final answer, but as a broad base from which to work out the three-dimensional relations. -

A large number of two-dimensional cascade tests have been run in this and other countries during the last 15 years. It is believed that, although the cascade configurations were geometrically two-dimensional, in no case except that of the porous-wall cascade of reference 1 was the

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NACA RN L51G31 _9_ 3

flow two-dimensional. This situation is ordinarily accepted on the grounds that the flow in the compressor is also subject to three-dimensional end effects. That similar end conditions would exist in stationary cascades and rotating blade rows seems unlikely. As discussed in reference 1, there is evidence, however; that the flow through typical axial compressor blades is more nearly like that in aerodynami-cally two-dimensional cascades than like that in cascades which are only geometrically two-dimensional. Excellent correlation between porous-wall cascade and rotor blade pressure-distribution and turning-angle values is shown for the design conditions of the compressor investigation reported in reference 2. The proper basic approach to - the compressor design problem, therefore, would seem to be to-separate the two-dimensional effects from the three-dimensional. This should also did in the evaluation of the separate effects of tip clearance and secondary flow in axial compressors. Figure-15 of reference 3, as well asunpublished data, indicates that design-angle data measured at low speeds are applicable at speeds up to critical. Therefore, a systematic series of low-speed cascade tests of the NACA 65-series compressor blade sections were made using the porous-wall technique to insure two-dimensionality of the flow. Test results and preliminary analysis are presented In this paper. -

/ SYMBOLS

a mean-line loading designation

b blade height or span, feet

c blade chord, feet

Ca section drag coefficient

CF resultant-force coefficient

Cj section lift coefficient

C 1 camber, expressed as design lift coefficient of isolated airfoil

CN section normal-force coefficient

CNM section normal-force coefficient obtained by calculation of momentum and pressure changes across blade row

CNp section normal-force coefficient obtained by integration of blade-surface pressure distribution

NACA RN L51G31

Cw wake momentum difference coefficient

F' force on blades, pounds

FM force on blades due to momentum change through blade row, pounds

F force on blades due to pressure change through blade row, pounds

Fw force on blades due to momentum difference in wake, pounds

g tangential spacing between blades, feet

P total pressure, pounds per square foot

p static pressure, pounds per square foot

q dynamic pressure, pounds per square foot

nondimensional static-pressure-rise' parameter

R Reynolds number based on blade chord

fP - p S pressure coefficient

-

U rotor blade rotational speed, feet per second

V flow velocity, feet per second

W flow velocity relative to blades, feet per second

x chordwise distance from blade leading edge, feet

y perpendicular distance from blade chord line, feet

angle between flow direction and blade chord, degrees

p3 angle between flow direction and axis, degrees

-.e - flow turning angle, degrees

Y angle between resultant-force direction and tangential direction, degrees

NCA RM L51G31 5

P mass density of flow, slugs per cubic foot

a solidity, chord of blades divided by tangential spacing

Subscripts:

a component in axial direction

d design, when used with angles

1 local

m referred to vector-mean velocity, Wm

u component in tangential , direction

s flow outside wake

1 upstream of blade row

2 downstream of blade row

APPARATUS, TEST PROGRAM, AND PROCEDURE

Description of Test Equipment

The test facility used in this investigation was the Langley 5-inch low-speed, porous-wall cascade tunnel described in reference 1 and shown in figures 1 and 2. During the course of this program some fur-ther Improvements were required to establish proper, testing conditions at higher pressure rise conditions. In particular, there was sufficient boundary-layer buildup behind the slot on the convex flexible end wall with high pressure rise cascades to cause separation and destroy simu-lation of the infinite cascade even though the blade flow was not separated. This was corrected by replacing the end wall with a porous flexible wall and suction chamber. In addition the large difference in flow length from the entrance cone to the side-wall slots between the tunnel ends at the higher inlet.alr angles gave quite different boundary-layer thickness along the length of the side-wall slots and made uniform flow entering the test section difficult to obtain. This condition was Improved by making the changeable side plates porous and drawing a small amount of air through them. The concave flexible end wall was made porous to provide a further control of flow conditions through the test section.

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The porous material found to be most satisfactoiy is commercial woven monel filter cloth. This is available in various meshes in widths up to 36 inches and can be calendered at the factory to reduce porosity and improve surface smoothness. The combination found most suitable for the present work was .a twill Dutch double weave of 30 by 250 mesh with warp wire-diameter of 0.010 inch and fill wire diameter of 0.008 inch. The original thickness of about 0.026 inch was reduced to 0.018 inch by calendering. The resulting material has the porosity characteristics shown in figure 3. The primary advantages of this material over others tried previously are its uniformity, flexibility, strength, 'surface smoothness, and relatively low cost.

Description of Airfoils

The blade family used in this investigation is formed by combining a basic thickness form with cambered mean lines. The basic thiOknesg form used is the NACA 65(216) -010 thickness form . with the ordinates increased by 0.0015 times the chordwise stations to provide slightly increased thickness toward the trailing edge. This thickness form has been designated the 65-010 blower blade section in references 4and 5. It was not derived for 10-percent thickness but was scaled down from the NACA 65,2-016 airfoil given on page 80 of reference 6. As discussed in reference 6, the scaling procedure gives the best results when it is restricted to maximum thickness changes of a few percent. Since the start of the program the NACA 65-010 basic thickness has been derived and is given on page 82 of reference 6. These basic thickness forms differ slightly but are considered to be interchangeable within the accuracy of the results reported herein. Ordinates for both the scaled and derived thickness forms are given in table I.

The basic mean line used is the a =.l.0 mean line given on page 97 of reference 6. The amount of camber is expressed in refer-ence 6 as design lift coefficient C2 0 for the isolated airfoil, and

that system has been retained. Ordinates and slopes for the a = l;o mean line are given in table II for C2 0 = 1.0. Both ordinates and slopes are scaled directly to obtain other cambers.- Cambered blade sections are obtained by applying the thickness perpendicular to the mean line at stations laid out along the chord line. The blade sec-tions tested are shown in figure 4. In the designation the camber is given by the first number after the dash in tenths of C i 0 . For example, the NACA 65-810 and NACA 65-(l2)lo blade sections are cambered for CI O = 0.8 and CI = 1.2, respectively.

NACA RM L51G3 1 7

Test Program and Procedure

Test program. - The test program was planned to provide sufficient information to satisfy any conventional vector diagram of the type shown in figure 5. Tests of 7-blade cascades were run with various combinations of inlet air angle 0 1 of 300 , 145°, 60° and 700, solid-ity a of 0.5, 0. 75, 1.0, 1.25 and 1.5, and cambers from C10 of 0 to 2.7 over the useful angle-of-attack : range. The most complete test series were run at solidities of 1.0 and 1.5; sufficient tests were made at the other solidities to guide interpolation and extrapola-tion. The combinations of 3, a, and blade section which were tested are tabulated in table III. The camber range covered at solidities of 1.0. and 1.5 was determined by one of two limitations. At the 11ghr inlet angles progressively higher camber8 xer.e use_un.ti1_the_1ijt loä ng ha been reached, that is, imtil the design condition coincided wffat lower inlet angles, however, desi n turni angle exceeded Inlet angle before. the limit loading had been reached and the tes s were terminated there. Limit conditions were attained at 1 3 = 70

0 , a = 1.0, 1. 25, and 1.5, and , = 600 , a =1.0 and 1.5.

Test procedure.- It was shown in reference 1 that two-dimensional' flow can be achieved by controlling the removal of boundary-layer air through porous test section side walls so that the downstream static pressure equals the. ideal valie, corresponding-to the turning angle, corrected for the blocking effect of the wake. This criterion was accordingly used in these tests. In addition, the flexible end wall shapes and suction flow quantities were adjusted to obtain uniform upstream flow direction and-wall static presures, criteria of two-dimensional flow simulating an infinite cascade. This procedure neces-sitated an approximate measurement of turning angle and wake size and an estimate of the correct pressure rise before the final settings could be made. Initially this required some cut-and-try procedure but after the initial tests at each 13 - a combination a chart similar to. figure 5 of reference 1 could be drawn to assist in estimating the pressure rise. An experienced operator could make the required esti-mates and settings very quickly using this procedure. Spot calcula-tions of the correct pressure rises were made after completion of tests to check the accuracy Of the values used.

Tests were made . at each cascade combination shown in table III over a range of angles of attack at intervals of 20 to 30• In general the tests covered the interval from negative to positive stall, where stall was determined by a large increase in wakesize. The prinQipal exceptions occurred for low cambered blades where negative stall would have occurred at negative turning. Itwas found that the small wall boundary-layer buildup for negative turnings and hence negative pressure rises would have required a less porous material than that norm all used, to avoid excess air removal while maintaining sufficient suction

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pressure differential to avoid local reverse flow through the porous material. It was not deemed worthwhile to change the porous material to obtain data in this relatively uninteresting range. For the NACA 65-010 section at 13 = 300 , however, the difficulty persisted well above 0 0 turning, and this combination was tested with both porous and solid walls.

The tests were entirely within a speed 'range considered incompres-sible. The bulk of the tests at solidities of 1.0 and 1.5 were run at an entering velocity ojeet per second. For the usual 5-inch blade chord, the Reynolds number was 214.5,000. Some information near the design point was obtained at higher effective Reynolds number for most cascade combinations by addingroughness to the blade leading edges in

the form of "41-inch-wide strips of masking tape draped around the

leading edges from wall to wall. In addition, some tests near design were run at a speed offeet per second and Reynolds number of 346,000 with and without roughness. Two cascade combinations were run at design over a range of Reynolds numbers from 160,000 to 11.70,000 to assist in estimating performance at Reynolds numbers other than the usual test value. In order -to provide further information on scale effects, two cascade combinations were tested through the 'a range with leading-edge roughness at the standard Reynolds number and in the smooth condition at a Reynolds number of 4 145,000. For solidities of 0.5 and 0.75 the tunnel could not accommodate -seven blades of 5-inch chord; the blade chord was reduced to 2.5 inches and the Reynolds number to approximately 200,000 for those tests. Tests with roughness were made near the design point for soliditiee below 1.0, but Reynolds numbers higher than 200,000 could not be obtained with the existing equipment.

Test measurements.- Blade pressure distribution was measured at the midspan position of the central airfoil at each angle of attack. In addition, surveys of wake total-pressure loss and turning angle were made downstream of the cascade. The total-pressure surveys were made with a nonintegrating multitube rake approximately 1 chord downstream of the blade trailing edges. Turning angle surveys were made by the "null method" with a claw type yaw head; since the yaw device was mounted on a track at the rear of the tunnel the distance from the blades varied from about 1 to 3 chords in the flow direction depending' upon the inlet- and turning-angle combination. Flow discharge angle readings were taken at a number of points downstream of several blade passages along the tunnel center line. These readings were averaged to obtain the final value. Since . the angle readings in the wake deviatd several degrees frcim the average reading, and the direction of the deviation varied consistntly with the direction of the total pressure gradient, the accuracy of readings in the wake was questioned. Therefore, the values obtained when the wake readings were included and excluded in the averaging prpcess were compared for a number of tests.

NACA RN L51G3 1

9

The resulting turning-angle curves compared very well, but there was con-siderably less scatter when only the readings outside the wake were used to obtain the turning-angle value. This latter procedure has been adopted as the standard method of measuring the flow discharge direc-tion. Upstream conditions were measured in the same manner as in reference 1.

Calculations. - Pressure distribution and wake-survey data were recorded and force values calculated nondimensionally as coefficients based numerically on the upstream dynamic pressure q 1 . This choice was dictated partly by convenience in reducing the data (standardiza-tion of q1 permits use of manometer scales which give nondimensional values directly) and partly by the belief that information based on entering flow is most convenient for design use, particularly when critical speed is important.

All forces due to pressure and momentum changes across the blade row were summed to obtain the resultant blade force coefficient CF1. In this process the wake total-pressure deficit was converted to an integrated momentum difference by the method given for the drag calcu-lation in the appendix of reference 6. This wake momentum difference, expressed nondimensionally, is designated the wake coefficient it represents the momentum difference between the wake and the stream outside the wake, and is based on q 1 numerically. The wake coeffi-cient Is not considered to be a true drag coefficient, but is used merely for, convenience in assessing the contribution of the wake in the sununation of forces.

The resultant-force coefficient was resolved into components per-pendicular and parallel to the vector mean velocity Mm (see fig. 5) to obtain the lift coefficient C1 1 and the drag coefficient Cd1, respectively. The mean velocity was calculated as the vector average of the velocities far upstream and far downstream. The velocity far downstream was obtained from measurements just behind the blades by using a momentum-weighted average of the velocity just behind the blades. This rather detailed method was found necessary to give con-sistent drag values. Since the resultant force Is very nearly perpen-dicularto the mean velocity, the value of the component parallel to the mean velocity is quite sensitive to mean-velocity direction. Attempts at using the downstream velocity outside the wake for aver-aging rather than the momentum-average velocity gave very erratic drag results indicating that mean velocity directions obtained in that manner were not reliable. In addition to the lift and drag, the blade normal-force coefficient CNN1 was obtained by computing the component

of the resultant-force coefficient perpendicular to the blade chord line. This normal-force coefficient was compared with the normal-force coefficient CNpl. obtained by integration of the blade surface

10 NACA RN L51G31

pressure distribution as a check on the accuracy of individual tests. A detailed derivation of the method of calculating the force coeffi-cients is given in the appendix.

Accuracy of results.- In general the turning-angle values measured

are believed to be accurate within near the design values. The

correlationprocedure used. is believed to have improved further the accuracy of the design values in the final results. For tests far from design, that is, near positive or negative stall, the accuracy was reduced somewhat. In addition, at an inlet angle of 700 'with sections of zero camber, satisfactory measurements were very difficult to obtain and the accuracy was reduced.

As noted in the section describing calculation methods, the blade normal-force coefficient CNM1 calculated from pressure-rise and

momentum considerations was dompared with the normal-force coeffi-cient CNp1 obtained, from the pressure distribution as a check on the

over-all accuracy of individual tests. Since these values would be affected by error in turning-angle, surface pressure or wake-survey readings, or by failure to achieve two-dimensionality of the flow, this comparison is a check on the over-all acceptability of the results. A difference of 5 percent between the two normal-force coefficients was set as the outside limit for acceptance of individual tests for lift coefficients above 0.2; below lift coefficients of 0.2 a direct numeri-cal comparison was made using a limit of plus or minus 0.01. The agreement was well within the 5-percent limit for most of the tests as originally run, and only a few conditions had to be repeated: The accuracy of the lift coefficients is directly comparable to that of the normal-force coefficients. The'accuracy of wake-coefficient and drag-coefficient values will be discussed later under Reynolds number effects.

PRESENTATION OF RESULTS

Detailed blade-performancedata for all cascade combinations tested are presented in the form of surface-pressure distributions and blade-section-characteristic plots in figures 6 to 84. The representa-tive pressure distributions presented have been selected to illustrate the variation through the angle-of-attack range for each combination. The section characteristics presented through the angle-of-attack range are turning angle, lift coefficient, wake coefficient, drag coefficient, and lift-drag ratio. The effects of changes in Reynolds number and blade-surface condition on section characteristics are given in figure .8. ' . ,

NACA RN L51G31 11

Trends of section operating range, in terms of angle-of-attack range, with camber for the four inlet angles tested are presented in figure 86. Variation of ideal and actual dynamic-pressure ratio across the cascade with turning angle and inlet angle is presented in fig-tire 87. Figure 88 gives the relation between inlet dynamic pressure and mean dynamic pressure for convenience in converting coefficients from one reference velocity to the other. Limit loading information is summarized in figure 89. Comparison of the present porous-wall-cascade turning-angle data with that of the solid-wall cascade of refer-ence 4 is made in figure 90 for a typical inlet angle and solidity combination. -

The information which is most useful for choosing the blade sec-tions to fulfill compressor design vector diagrams is summarized in figures 91 to 111 inclusive. The variation of turning angle with angle' of attack for the blade sections tested is presented for one combina-tion of inlet angle and solidity in each of the figures 91 to 106. Trends of the slopes of the turning-angle, angle-of-attack curves near design are given in figure 107. Figures 108 to 111 are design and correlation charts; the variation of design turning angle anddesign angle of attack with the parameters, camber, inlet angle, and solidity, is presented for several combinations of the parameters so that interpolation to the conditions of a design velocity diagram is relatively easy.

DISCUSSION

Design Conditions

The values and shape of the blade-surface-pressure distribution are important criteria for predicting the conditions of best operation at high Mach numbers. Velocity peaks occurring on either surface in low-speed tests would be accentuated at high speeds, and supersonic velocities with attendant shock losses would occur at relatively low entering Mach numbers. The selection of the angle of attack designated as "design" for each combination of inlet angle, solidity, and camber is based on the premise that the blade section will be required to operate at Mach numbers near the critical value. The trend of pressure-distribution shape over the angle-of-attack range was examined for each cascade combinatiofl, and the angle for which no velocity peaks occurred on either surface r was selected as being optimum from the standpoint of high-speed usage. In general the design angle so selected is near the middle of the low-drag range thus indicating efficient section opera-tion for angles a few degrees higher or lower than the design condi-tion. The design-angle-of-attack choices are indicated by an arrow on the blade-section-characteristic plàts of figures 6 to' 84. The'design

12 . NACA RN L51G31

angles are also shown by cross bars on the turning-angle summary curves in figures 91 to 106.

Correlation of the design angles of attack and design turning angles over the range of camber, solidity, and inlet angle is given by figures 108 to ill in a manner convenient for design use. The correla- tion is excellent; smooth curves result when any two of the three parameters are used as independent variables. It should be noted that the design angle of attack is the same for all inlet angles at any given solidity and camber.

The section-characteristic curves of figures 6 to 84 indicate that, in general., the design points chosen do not give maximum lift-to-drag ratios for low- and medium-speed operation. For designs which will not operate near critical speed, therefore, higher efficiency could be obtained by using angles of attack several degrees higher : than the design points presented. This procedure must be used with caution at the higher camber and inlet-angle combinations, however, since the sec-, tion operating range becomes quite narrow for combinations of highest camber and inlet angle corresponding to the highest values of Ap/q1. It is recommended that the individual pressure distributions and section-characteristic curves be examined before departure from the specified design points is made.

Reynolds Number Effects

Pressure distribution and boundary layers. - For many of the tests at angles of attack near and below design, there is evidence that a region of laminar separation of the boundary-layer flow occurred on the convex blade surface; this separated boundary layer then became turbu-lent and reattached to the blade surface as a relatively thick turbu-lent boundary layer. The mechanism of such a flow sequence is described for the isolated airfoil in reference 7. The laminar separation is indicated by a relatively flat region in the pressure distribution and the turbulent reattachment is characterized by a rapid pressure recovery just downstream of the separated region. This flow pattern can be seen clearly in many of the figures but it is particularly evident in fig-ures 2(a), 42(c), 56(b) to 56(d), and 66(a) to. 66(e). For some tests, it appears that laminar separation occurred on the concave surface as well. This is noticeable in figures 42(b), 112(d), 42(e), 66(c), and 66(d).

The extent of laminar boundary-layer flow which occurs on an air-foil surface is. affected by Reynolds number, stream turbulence level, airfoil surface condition, and surface pressure gradient. Increases in Reynolds number, stream turbulence, and surface roughness would promote earlier transition. Qualitatively a gradient of decreasing

NACA RM L51G31 13

surface pressure would be required to maintain laminar flow if the Reynolds number, stream turbulence, surface roughness, or the combina-tion of these, which might be referred to as "effective Reynolds number," were high enough to favor transition. At the turbulence level of the 5-inch cascade tunnel, however, laminar flow and laminar separation on the convex surface persisted to Reynolds numbers up to 245,000 even when the surface pressure gradient was slightly unfavorable. The addi-tion of leading-edge roughness, as described in the "Testing Methods" section reduced the extent of the laminar separation region, but did not eliminate it in some cases. In view of the thick boundary layer which results from laminar separation and reattachment, it appears that the minimum final boundary-layer thickness and section drag coefficient would result if the Reynolds- 'number and turbulence values were such as to cause transition before laminar separation occurred. Use of leading-edge roughness to reduce an extended laminar separation region would probably result in a thinner final boundary layer than that for the smooth blade at the same Reynolds number but would probably result in a thicker boundary layer than that for the smooth blade at high Reynolds number. A thick turbulent boundary layer would be expected to promote turbulent separation near the trailing edge of compressor blades which produce a significant pressure rise.

Wake coefficient and drag coefficient.- As noted previously, the wake coefficient Cw1 expresses the momentum difference between the wake flow and the downstream flow outside the wake in a manner conven-ient for use in summing blade forces. The wake coefficient is, of course, directly dependent upon boundary-layer thickness and shape, and changes in the boundary layer with changes in effective Reynolds number are reflected in the wake-coefficient values. Furthermore, if the effective Reynolds number is near the condition where laminar separa-tion may or may not occur, the change in surface pressure gradient with change in angle of attack would control the presence and extent of laminar separation on either blade surface. Obviously erratic varia-tions in the value of the wake coefficients would result under those circumstances. The blade-section-characteristic curves of figures 6 to 84 show that in most cases the wake-coefficient values were irregular as the angle of attack was varied in the region near design at the usual test Reynolds number of 245,000: With higher Reynolds number and/or leading-edge roughness the rapid local pressure recovery associated with boundary-layer reattachment was less evident in the surface pressure-distributions and the wake coefficient usually was reduced. For ,a few cases, notably those of figures 34(g), 35( g), 68(g), and 84(g), leading-edge roughness increased the wake coefficient, however; in those cases the roughness apparently produced a more severe turbulent boundary Layer than laminar separation and reattachment did.

The trend of drag coefficient C d1, defined as the component of -esultant force parallel to the mean-velocity, was similar to that of

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wake coefficient. The drag curves were quite irregular near design - angle of attack and the values measured varied as much as 30 percent with Reynolds number and roughness. Obviously the values of both drag coefficient and lift-drag ratio near design are not sufficiently reliable to use directly in a design analysis. These values should be of some use for comparison purposes, however. The large drag rise associated with positive and negative stall should be relatively insen-sitive to Reynolds number 'effects, because the pressure gradients on-the critical surfaces are then unfavorable to laminar flow, and so should be useful for determining effective operating range.

The trend of drag coefficient with Reynolds number near the design condition for the NACA 65-(12)10 blade section at f3 of 60°, a of 1.0, and 3 of 450 , a of 1.5 shown in figure 85(a) serves to indicate the magnitude of the Reynolds number effect. Increasing the stream turbu-

lence by the use of a 1_inch_mesh screen upstream of the test section

• lowered the drag coefficients at low Reynolds number, and reduced the Reynolds number at which the drag coefficients become essentially con-stant with Reynolds number. The comparison of Cd values through the angle-of-attack range for the same cascade combinations at two Reynolds numbers in figures 85(b) and 85(c) gives some further indication of Reynolds number effect. For R of 445,000, the drag coefficients are lower and the curves are smoother than for R of 245,000. The addi-tion of leading-edge roughness in figure 85(b) smoothed the drag curve but did not give the same decrease in' drag that the high R did. There appears to be some effect on the angle of attack at which the drag rises rapidly in figure 85(c) 'but since the effect was not the same in figure 85(b) no conclusions can be drawn.

Turning angle and lift. - Figure 85( a) shows that the effect of Reynolds number on turning angle near design a. is almost insignifi-cant for R between 220,000 and 470,000. This is borne out by the fact that throughout figures 6 to 84 changes in e with Reynolds num-ber and roughness were, in general,. within the limits of measuring accuracy. Below R of 220,000 a decrease of design turning angle can be expected. There appears to be some R effect on turning angle near stall in figure 85(c), but again the effect has not been definitely established. It can be concluded that the design turning angles pre-sented are correct for R above 220,000, but that the effect of R near stall is unknown. •

Laminar separation had no apreciable effect on the measured lift. The lift-coefficient values for a given test agreed well at low and high Reynolds numbers and with and without roughness. The normal-force coefficients obtained by integration of the pressure distributions also changed very little with changes in Reynolds number and roughness.

NACA RN L51G31 15

Operating Range

In order to estimate the useful operating range of the various sections at the several solidity and inlet angle conditions tested, Howell's index of twice the minimum drag (reference 8) was used to select the upper and lower limits of angle of attack. As discussed previously\in the section concerning Reynold's number effects, the accuracy of the measured values of drag coefficient near design angle of attack suffered due to laminar-flow separation. The minimum value of drag coefficient could not be determined exactly and an approximate value was used todetermine the operating range. For most of the test configurations, the drag coefficient changed rapidly with angle of attack near, the ends of-the useful range, so an error in the value of minimum drag used would have only a small affect on the operating range value. Some scatter in the results was evident, however.

No' Most values at constant camber and inlet angle fell within the scatter of the points. A tendency for the range to increase slightly as the solidity was Increased was detectable at 13 = 150, but this was not evident for other inlet angles. The results plotted In figure 86 indicate that the major determinant of operating range is inlet angle. As the Inlet angle is increased, the usable range of angle of attack is decreased, with greater changes indicated for angles above design than for angles lower than design. The camber of the section affects the operating range in the following manner for angles of attack above design: at an inlet angle of 30° f the range increased with increasing camber; at inlet angles of 14.50 , 600 and 70 , the opposite trend occurred. For values of 'a less than design, little change in range with camber was indi- cated for 13 =300; at higher inlet angles, the range decreased-as the section camber increased.

With high entering velocities, the section operating range would be reduced due to a more rapid increase of drag at angles of attack well above or below design. Further, the comparison, between sections of different camber, at constant inlet angle and solidity, would be altered as the flow velocities relative to the blade surfaces exceed the local velocity of sound.

Pressure Rise

The ideal, nondiinensional pressure rise p/q 1 - across a two-dimensional cascade , is specified when the inlet angle and turning angle are known, since the ratio of the flow areas determines the pressure rise. Since-the mass flow is consiant, the actual pressure rise is less than the ideal because of the "blocking" effect of the wake on the downstream flow area. For given inlet and turning angles,-the

16 NACA RM L51G 31

• blocking effect would be more severe for higher solidity, since the unaffected flow area is reduced. For incompressible flow the nondimen-sional pressure rise is equal to one,minus the dynamic-pressure ratio,

that is, = 1 - -& The actual dynamic-pressure ratio becomes

higher than the ideal because of the wake blocking effect. The ideal dynamic-pressure ratios, and the actual ratios at design turning angles for two solidities, are sunmiarized in figure 87 for the range of inlet and turning angles tested. The dynamic-pressure ratios for individual tests are given by the short bars at the 100-percent points of the pressure-distribution plots. Wake blocking effects would be changed by the same Reynolds 'number and roughness factors which change the wake coefficient; however, the percentage change in dynamic-pressure ratio would be small.

/

Limit Loading

Information on the maximum loading which can be achieved in a com-pressor blade row is important in the design of high performance axial-flow compressors. As noted previously, the high pressure rise associated with large turning at high inlet angles promotes turbulent separation so that at inlet angles of 600 and 70° the stall angle of attack moved progressively closer to the design angle with increasing section camber. The limit turning Is reached when the maximum turning is no greater than design turning. The practical limit would be somewhat lower to give a reasonable operating range. -

Approximate limit turning was reached at 13 of 6o°, a of 1.0 and 1. 5, and at 13 of 700, Cr of 1.0, 1.25, and 1. 5. Information from those tests is given in terms of a commonly used loading parameter, aCim,

in figure 89. Both the actual test values of the parameter, and the ideal values calculated using the test inlet and turning angles are presented. Note that the lift coefficient is here based, numerically, on the mean velocity, to conform to the usual form of theparameter.

Arbitrarily chosen constant values of clC jm have often been used

as maximum allowable values in design analyses. The fallacy of using 'any constant value as a limit is clearly shown in figure 89; the true limiting value increases with increasing solidity and decreases with increasing inlet angle. Since no limits were reached for inlet angles of 15° and 30°, it is clear that the limitation has very little signif-icance there except, perhaps, at very low solidities. The phenomenon is not yet well enough understood to permit the choice of a parameter which could define the over-all limitation as a single value.

V

4

NACA RN L5 1G31 - 17

Comparison with Solid-Wall Cascade Data

The comparison between pressure-distribution and turning-angle data for a solid-wall cascade tunnel and for the present porous-wall cascade tunnel is given in reference 1 for the NPLCA 65-(12)10 blade section at 1i of 600 and -a of 1.0. The comparison has been extended in fig-ure 90 to include turning-angle data for all the cambers reported for

of 600 and a of 1.0 in reference 4. The turning-angle curves compare fairly well for cambers up . to C1 0 of 0.8, but beyond that the

data of reference 4 deviate significantly from the present results. Comparisons at other conditions would show similar trends.

Turning Angle, Angle-of-Attack Relationships

Summaries of the turning angle, angle-of-attack relationships through the caniber range are given for each inlet angle and solidity. in figures 91 to 106. The variations are quite consistent for most of the range. Some inconsistency in the shape of the curves at stall is a result of reduced accuracy of measurement there. For combinations giving moderate pressure rises there are straight-line relationships for considerable portions of the curves. For the highest pressure rises, however, there are no definite straight-line relationships. The variation of the elopes near design is given in figure 107 to assist in estimating relationships at conditions other than those tested. These slopes are average slopes for the camber range, and do not apply for the highest cambers. Theymust be used with particular caution for inlet angles near 700, since very narrow straight-line regions are prevalent there.

SUMMARY OF RESULTS

The systematic investigation of NACA 65-series compressor blade sections in a low-speed cascade tunnel has provided design data for all conditions within the usual range of application. The results of this investigation indicate a continuous variation of blade-section perform-ance as the major cascade parameters, blade camber, inlet angle, and solidity are varied over the useful range. Summary curves have been prepared to facilitate selection of blade sections and settings for compressor-design velocity diagrams for optimum high-speed operation.

- Upper limits for the loading parameter aCI m have been established

for some conditions, and the invalidity of using a constant value of the parameter has been shown.

18 NACA RN L51G31

The variation of the useful section operating range with camber, inlet angle, and solidity has been shown. The operating range was found to be broad except for the highest pressure-rise conditions.

Langley Aeronautical Laboratory National Advisory Committee for Aeronautics

Langley Field, Va.

NP&A RN 1,51G31 19

APPENDIX

/ CALCULATION OF BLADE FORCE COEFFICIENTS

The two-dimensional resultant force on a blade in cascade is the vector sum of all the pressure and momentum forces exerted by the fluid. At any appreciable distance behind the blade row the static pressure is constant along a line parallel to the blade row, since any prior pres-sure gradients would have been converted to momentum changes. Assuming a pressure force acting in the upstream direction to be positive:

FP = (P2 -('i)

Sum momentum forces In the axial and tangential directions. Assume axial momentum forces positive if the force on the blade is in the upstream direction, and tangential momentum forces positive If t

' he

tangential velocity change is in the usual direction shown in figure 5. The axial momentum force then is

'M =f P2Va2 ( Va2 - Va1)b dg (2) g.

and the tangential momentum force is

• F = f P2Va2(11u1. - w)b dg (3)

Since momentum values In the wake can be obtained most easily as differ-ences between the wake values and the downstream value outside the wake, it is convenient to rewrite equations (2) and (3)

F Ma= PihTa1 ( 1a2 - s1a1)t +f P2Va(Va - Va2 )b dg ()

F. Plval(Wu1 wu2)b + P2Va2(WU25 - W)b dg (5)

But the wake momentum force, as calculated from. wake surveys, is

20 NACA RN L51G3 1

F f P2Va2 (W2 - w2 )b dg (6)

If, now, the flow direction In the wake can be assumed to be the same as the average downstream flow direction, the wake force can be resolved into components In the axial and tangential directions. Using the same sign convention as before

Fwa w cos 2 =fg P2

Va2 ('Ts,2, - Va)b dg (7)

= Fw sin 02 = r P2Va2 ( 1u2 - w 2 )b dg (8)

Jg

These are the integral terms in equations (4) and (5). Substituting equation (7) in equation (4) and equation (8) in equation (5), the axial and tangential force components become

Fa = F + FMa = (P2 - p1)bg + PfTai(1a2 - Va1)b - Fw cos

FU = F = PlVal(Wul - wu2 )b + FV sin 02

For convenience use coefficients based on q1

Fa =+ 2V a1(2s - Va

CFa1.1W12bc a L1 w12

- C COB

F2Val - )1

I+C sin 02 CFu1 .ipW12bc

The resultant-force coefficient is given by

C = 2+c 2 Fl ^CFa1 u1

NCA B14 L51G31 21

If y is used to denote the angle between the resultant force and the tangential direction

C -1

y=tanPa 1

Pu1

The lift coefficient C1 1 and drag coefficient Cd1 are the com-

ponents of Cp1 perpendicular and \parallel to the vector mean velocity,

Wm, respectively, where Wm is the vector average of the velocities far upstream and far downstream. The upstream velocity can be easily measured. The velocity far downstream Is obtained by proper averaging of the velocities just behind the blades. Since the axial area controls the axial velocity, conservation of mass determines the axial component of the velocity far downstream. Since there are no physical boundaries in the tangential direction to support pressure gradients, conservation of momentum controls the tangential component far downstream. The dis-cussion up to this point applies to compressible as well as incompres-sible flow.

For compressible flow the effect of wake mixing on pressures and densities makes accurate determination of the axial velocity far down-stream rather tedious. In the incompressible, two-dimensional case the downstream axial component is Va l, and the downstream tangential com-

ponent is the .Momentum-weighted average of Wu2. This tangential com-

ponent can be obtained by adding to the tangential momentum of the dis-charge free stream the integrated tangential momentum of the wake. The integrated tangential momentum of the wake can be determined from the tangential component- of the wake coefficient. Having the correct. velocity far downstream, the vector mean-velocity direction Wm can be easily obtained. The direction of Wm should be determined accurately since - Cp1 is very nearly perpendicular to Wm, and the value of the

drag component Cd1 is sensitive to small changes in the direction of Wm.

22 NACA RM L51G31

REFERENCES

1. Erwin, John R., and Emery, James C.: Effect of Tunnel Configuration and Testing Technique on Cascade Performance. NACA TN 2028 1 1950.

2. Westphal, Willard R., and Godwin, William R.: Comparison of NACA 65-Series Compressor Blade Pressure Distributions and Performance in a Rotor and in Cascade. NACA RN L51H20, 1951.

3. Bogdonoff, Seymour M.: N.A.C.A. Casôade Data for the Blade Design of High Performance Axial-Flow Compressors. Jour. Aero. Sci., vol. 15, no. 2, Feb., 1948, pp. 89-95.

4. Bogonoff, Seymour M., and Bogdonoff, Harriet E.: Blade Design Data for Axial-Flow Fans and Compressors. NACA ACR L5FO7a, 1945.

5. Bogdonoff, Seymour M., and Hess, EugeneE.: Axial-Flow Fan and Compressor Blade Desin Data at 52.5 0 Stagger and Further Verification of Cascade Data by Rotor Tests. NACA TN 1271, 1947.

6. Abbott, Ira H., Von Doenhoff, Albert E., and Stivers, Louis S., Jr.: Sunniary of Airfoil Data. NACA Rep. 82 14, 1945. (Formerly NACA ACR L5CO5.)

7. Bursriall, William J., and Loftin, Laurence K., Jr.: Experimental Investigation of Localized Regions of Laminar-Boundary-Layer Separation. NACA TN 2338, 1951.

8. Howell, A. R.: Design of Axial Compressors. Lectures on the Development of the British Gas Turbine Jet Unit Published in War Emergency Issue No. 12 of the Institution of Mechanical Engineers. A.S.M.E. Reprint, Jan. 1947, pp. 1452-1462.

I I

i

NACA RN L51G31

23

TABLE I

ORDINATES FOR NACA 65-010 BASIC THICKNESS FORMS

[Stations and ordinates in percent of chordi

ri

Station, xOrdinates, ±Y

65(216)-010-airfoil ;ombined Derived 65J010 airfoil with y = 0.0015x

0 1 0 0 . 5 .752 .772 .75 .890 .932'

1.25 1.124 1.169 2.5 .. 1.571 1.574. 5.0 2.222 2.177 7.5 2.709 2.647

10 3.111 . 3.0140 ITS 3.746 3.666 20 4.218 4.143 25 . 4.570 4.503 30 4.824 .. 4.760 35 . 4.982 4.924 40 5.057 . 4.996 45 5.029 4.963 50- . 4.870 4.812 55 4.570 4.530 .60 . 4.151 4.146 65 3.627 3.682 70 . 3.038 . 3.156 75 2.451 2.584 80 1.847 1.987 85 1.251 1.385 90 - .749 .810 95 .354 .306

100 .150 0 L.E. radius .666 .687

w

24 NACA RM L51G31

TABLE II

ORDINATES FOR THE NACA a = 1.0 MEAN LINE

[Stations and ordinates in percent of chorj

Cj =1.0

Station, x Ord'inate,t y Slope, dy/dx

.250 0.42120 .75 .350 .38875

1.25 .535 .34770 2.5 .930 .29155 5.0 1.58o .2330 7.5 2.120 .19995

10 2.585 .17485 15 3.365 .13805 20 3.980 .11030 25 4.475 .08745 30 4.86o .o6745 35 5.150 .O925

5.355 .03225 5.75 .01595

•50. 5.515 0 55 5.475 -.01595 6o 5.355 -.03225 65 5.156 -.04925 70 4.860 -.o6745 75 4.475 -.08745 80 3.980 -.11030 85 3.365 -.13805

.90 2.585 .171485 95 1.580 -.23436

100 0

/

1.0mowt-

NACA RN L51G31 25

TABLE, III

CASCADE COMBINATIONS TESTED

(deg)

30 45 60 70

65-410 65-4io .0 . 50 65-(12)lo 65-(12)10

6-(18)io 65-(18)10

65-410 65-410 .75 65-(12)lo 65-(12)10

6-(18)io 65-(18)io

6-010 65-010 6-010 65-010 6-410 6-410 65-410 65-410 65-810 65-810 65-810 - 65-810 65-(12)10- 65-(12)10 65-(12)10- 65-(12)10-

1.00 6-(15)10 65-(15)10 65-(15) 10 a65(15)10 • 65-(18)io 65-(18)io 65-(18)10

65-(21)10 65-(21)10 65-(24)10 65-(27)10

65-410 65-410 65-410 65-410 1.25 65-(12)lo 65-(12)lo 65-(12)lo 6-810

65-(18)lo 65-(18)10 65-(18)lo 65-(12)10 65-(1)10

65-010 6-010 6-010 6-010 65- 410 65-410 65-410 65-410 65-810 65-810 65-810 6-810

1.50 65-(12)lo 65-(12)10 65-(12)10 65-(12)10 65-(15)10 65-(15)10 65-(15)10 65-(15)10 65-(18)iO 65-(18)io 65-(18)lo

65-(21)lo 65-(21)10 65-(24)lo 65-(24)10

No design point was obtained for this combination.

CH

0

0 •r-1

C) C) CD

IC

C) a)

U (I)

H a, C-)

•1-1

11)

CD

CD 0

C-)

NACA RM L51G31

Cd

C)

H bD

cdc

r-i co

IC H H

C)

H

C)

Va, C)

C)

a)

a)

I H

0 0 k 0 p4

0

0 •1-4 m

rj

C.

-PC)

H

r

Cd çi

J

1W IC"

0

4)

a)

Cc

a)

a)

PA CO

tai

p c'J

All

I

OA HT 73 0

NACA RM L71G31

27

28 NACA RM L1G31

U' CsJ

4.) 0

H C.)

r1

H a)

0

CsJ

a),

a)0

. +)

(D0 cc

. a)r —

o•rl

- CO

01

Q, '. D)

4.) . Od

CL

Ci

-i-I I:')

0

a)

Cli OD 1.0 Ict

s/U 11001 9A IDWJON

e.J .oWu

we

NACA RN L51G31 29

Chord

-I----- "—Tangent

NACA 65-010

Chord

NACA 65-410 "—Tangent

Chord

Tangent NACA 65-810

). Chord

Tangent NACA 65-(12)10

(a) Lower cambered sections. Angle between chord line and tangent to lower surface as shown for the various sections.

Figure 14• - Blade sections tested in this investigation.

30

NACA P.M L51G31

Chord

NACA 6-(15)10 Tangent

Chord

NACA 6-(18)10 Tangent

Chord -

• NACA6-(21)1O Tangent

1IIIIT Chord

- NACA 6-(2I)10 Tangent

Chord

NACL6-(27)10

(b) Higher cambered sections. Chord line and tangent line coincident.

Figure 1. - Concluded.

NACA RM L51G31

31

Figure 5.- Typical vector diagram for a compressor rotor.

Va

'I

.8

. 8n 00 20 40 60 80 IC

.1

MEN

1.6

S .8

0

1.6

S .8

0 0 20 40 60 RO 100

2.4

S 1.6

.8

0

24

S 1.6

(-I

32

NACA RM L51G31

2.4

1.6

1.6 S

S

Percent chord Percent chord

(a) ar- 3.0°; 8= -3.4° (b) a 1 = 3.0°; 8= 2.4? o Convex surface c Concave surface

Percent chord Percent chord (c)a1=4.0°; 8= 2.9? (d) a1 = e.o°; 8=6.9?

020406D80100 020406080K0 Percent chord Percent chord

(e) a 1 = 11.0 0 8 = 9.30? - (f) a 1 = 17.0°; 8 = 14.3?

Figure 6.- Blade-surface pressure distributons and blade section charac. teristics for the cascade combination, Pi =

3Q0, .1.00, and

blade section, NACA 67-010.

MACA RM L51G31

33

20 .5

16 .4

12 - .3

8_.2

deg -

4_.I

-8 -

0•I8

- p C21 - _-I-- -

* Cd1

A ew, 7• —y — -•--

IIIIIZ2^II

40 .07

30 .06

ao —1 .05

10 .84

- - C 0 - .03

•0 —'.02

0 - .01

r •—n

-

-4 0 4 8 12 16 20

a deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 6.- Concluded.

1.6

S .8

0

1.6

S .8

0

3J.. NACA RM L1G31

1.6

S

S

.8

0

Percent chord Percent chord (a) a 1 = 3.00; 8 = 0.2? (b) a = 3.00; 9= 5.6?

o Convex surface a Concove'surfac

.8

0

Percent chord Percent chord (c) a=75 0; o r-9.9! (d) a1 : 9.0°; 8 = 11.3?

S 1.6

.8

00 20 40 80 80 100 020406080100

Percent chord Percent chord (e) a1: l5.Q°; 8 : 16.60 (f) a1: 21.0°; 8 = 21.1°.

Figure 7.- Blade-surface pressure distributions and blade section characteristics for the cascade conth1nat1, =30'1 a = 1.00, and blade section, NACA 65-41o.

3.2--- I

24---__

\ .s I.6—------

SO .05

50 —1 .04

;o —1 .03

30 - .02 Icw

I Cdl —1 .01

0 —i .01

NACA RN L51G31 .. 35

28r— 1.7

24F— .6

20 .5

16 .4

.O,deg H c11

l2— .3

8 .2

4 .1

o 1 I I IV .1 I I I I I I I 10 0 4 8 12 16 20 2

deg

(g). Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 7.- Concluded. -

I. S

Ii .11

-o I-'ercent chord Frcent chord

(a) a = 2.40; 9 = 350 (b) a 1 : 3.70; 9: 9.3°

o Convex surface o Concave .surface

I

U Ii

: S .8 S

36

NAA RM L1G31

2A

1.6

S

.8

o 20 40 60 80 00 20 40 60 80 ibo Percent chord Percent chord (c) a,: 6.70 ; 8=12.3? (d) a,: 9.7 0 ; 8=15.0?

a4

S 1.6

.8

0

3.2--I

24

NACA

S I.6—---

a----

a

0 20' 40 GD 80 100 0 20 .40 60 80100 Frtent chord Percent chord

(e) a 1 = 15.70; 8: 20.5° r-- i(f) a 21.70 ; 8 : 25.00.

Figure 8.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 300,

Cr = 1.00, and blade section, NACA 65-810.

NACA RN L51G31 Tr . 37

.1

28

24 .4

/

" 20

O,deg c

16

12

8•

4

n

80

70 .07

.06

50 .05 Cw

Ek

Cd,

40 .04

30 .03

20 .02

10 .01

=4 0 4 8 12 16 20 24

a/, deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 8.- Concluded.

- -....----- ..

24

1.6 S

.8

2.4

1.6 S

.8

38

NACA RN L1G31 -.-----

o 20 40 60 80 ibo ''Ô 20 4060 80 ibo Percent chord Frcent chord

(a) a =4.1 0 ; 9 : 12.8° (b) a 1 : 10. 1 0 ; 9=1880

o Convex surface o Concave surface

S

0 20406080100

Percent chord Percent chord

(C) a,: I3.I 8 :2170 (d) a 1 :18J°; 9:26.3?

4.98

3.2

P-4

S 1.6

.8

0

1.6

S .8

- 0

S 1.6• .

0

3.2-- I I

24---

—---

"Old I

rO-IITI0 20408D80 100 Th

Percent chord (e) a 1 24.1°; 8:31.2 0. ___ (f)

Figure 9.- Blade-surface pressure distributins characteristics for the cascade combination, and blade section' 65-(12)10.

20 40 60 80 100 Percent chord

a,: 30.10; 9:340?

and blade section = 3Q0,= 1.00,

NACA RN L51G31

39

o o 0Co

0 00 N - 0 Q

I •I I I I I I I 0

T--1 o 0 0 00 -110 0 0 0 0 10 N

10 ---

--- --------cu H -- --- -----

CP

N

---4---

A - ---11---! •0 ------- 0 40

.D-.

/ N -k- ------

In

0 CP

--ç /N

-00G44

-j 0 -

Ii... II • I! • I• Ill• II••I o ID N 0 0 w N

10 10 N . N 04 - -

a,

U 0

C-)

-0 --

S

1.6 S

.8

MM I

U a

I I I I ) 20 40 60 80 IC

Ure NACA EM L51G31

iercent ctord Percent chord (a) a 1 : 5.00 ; 8=16.5! (b) a 1 =II.0°; 8=23.2°.

o Convex surface c Concave surface

1.6

S 8

1.6

0

-

-o u 'K.) bO 80 100 0 20 40 60 80 100 Percent chord Percent chord

(C) a 1: 15.0°; 8 : 26.7! (d) a 1=17.OP ; 8*28.60

3.90

S I

cvL

3.2--

24i _

NACA

S l.6-----

----s-

8----

--a/

-0 20 40 60 80 100

Frtent chord (e) ' a 1 : 23.00; 8: 34.I.

Figure 10.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(15)

0 20 40 60 80 00 Percent chord

a 1 29.0°; 8:38.21

distributions and blade section combination, 0 1 = 30°, -a = 1.00,

LO.

NACA RM L51G31 41

o 0 0 0O0 0 0

I I I I I I I I I I I 2 0 0

/

C) a

a

CO N0U'

CP C -

N 21

0U'C H

c_) N

- 0

0- 0, 40

H

(0

NC) o ' I.. a

0 C

co

9 O C in

• I I •1 I I I I I CD

- 0 CD N

IC)0 N N

0 W

.8

I 11 ) 20 40 60 80 IC ---4 I -

S 1.6

.8

a

S I.E

(1

14.2

NACA RM L51G31

z 14 -1

VQ

2.4

1.6

1.6

S

S

rerceni cncra Percent chord (a) a 1 : 10.00; 8 : 23.1°. (b) a 1: 16.0°; 8 =29.70

o Convex surface o Concave surface

•IUUEPercent chord

(C) a l z 18.00;

3.2

a4

I.E

- S .8

I 1 I D 20 40 60 80 Ic

I-'ercent chord (d) a 1 =23.0°; 8=36.1°

3.2

2

1.6

S • .8

0

0 20 40 60 80 tOO -- trcent chord Percent chord (e) a,= 29.00; 8= 40.9° (f) a 1 : 35.00; 8 42.6°

Figure 11.- Blade-surface pressure distributions and blade section characteristics for the cascade combiation, =300,a = 1.00, and blade section, NACA 65-(18)io.

NACA RN L51G31 43

52 —I.

48 —I.

44 —l.

40 —Ii

8, deg \Z

36 -1.1

•32 —t.c

28 -.9

24 -.8

20 -.7

- I 0 9

o C1

. C,1

8( Cd1------

-

---

- --

- - -

-

- -._ 6(

_- --.- -

-v----- .-- 3C

-

- - .-.-- - - -

-/-

-- 2C

iZ 16 20 24 28 Th Th

1--j.07

.06 I—

—H .05

—Ia Icd1

—1 .04

—1 .03

.02

0I

RI

a1 , deg

(g) Section characteristics ; arrow shows design angle of attack flagged symbol indicates leading-edge roughness.

- Figure 11.- Concluded.

a4

S 1.6

.8

0

3.2

24

S 1.6

.8

(•1

ia

1.6

S

.8

-

laws=&

NACA RN L5101

-

S

.8

1.6

S .8

0

0 20 40 60 80 100 "0 20 40 60 80 ibo Percent chord Percent chord

(a) a 1: 0.00; 9 :2.4? (b)a1: 6.00;

o Convex surface Concave surface

1.6

S .8

0 0 20 40 60 80 100

Percent chord Percent chord (c) a,: 8.0°; 9 10.6°. (d) a ,= I0.00;9:

3.51

'+0 w tso IOU 0 20 40 60 80 100 Percent chord Percent chord

(e) a , : 16.0 0 ; 9 : 160 0 . (f) a,: 22.0° ; 8 22.9°.

Figure 12.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, i•= 300,

1.25,

and blade section, NACA6541O.

• 32 .7

28 .6

24 .5

20 .4

16 .3

Cl'

l2.2

8 k—.1

4 L.

NACA RM L51G31

".5

I I I I' I ii I I I I I I - -4 0 4 8 12 16 20 24

a1 , deg

(g) Section choracter.istics ; arrow shows design angle of attack; flagged symbol indicates leading - edge roughness.

Figure 12.- Concluded.

.. .

80 - .09

70 —1 .08

60 —1 07

5° H .06

40 —I .05 IC Wi

DlcdI

30 —A.04

20 .03

10 .02

0 ---1.01

LE

S .8

0

46

NACA RM L51G31

2

1.6 LE S S

.8 .8

0 20 40 60 80 100 0 2040 60 80 100 Percent chord Percent chord

(a) a 1 = 4.1 0 ; 8 13.9 0. ( b) a = 10.1° 8 19.9°. o Convex surface O Concave surfarp

M'SII

I-'ercent chord (c) ai:13.10;8=22.7o,

I.E

S . .8

911ROW, IM-70m: so,FA

Percent chord (d),z 15.1 0 ; 8=24.50.

3.2 I

24J I I

S 1.6

.8

0

S

.8 FE39

'I 0 , 20 40 GD 80100 0 Frcent chord

(e) a 1 = 23.1°; 8 31.9°. _______________

Figure 13.- Blade-surface pressure distribution characteristics for the cascade combinatin, and blade section, NACA 65-(12)10.

20 40 60 80 100 Percent chord

a, = 32.I'°;8= 38.3°.

s and blade section 30°, a = 1.25,

U 0

0

-

C

0' • 0

0' u,C

.0

11 C

U

a)

rl 0

0 0

.7-I

NACA EM L51G31 - 47

cJ - o 0 0 00 00 0 Q

I o o

I I . 1 0

I I I 0

I I I I I 0 0

40 2

- - --- -

- -__z-- - --

NN-----'

It --

- -CQ

-

----

-

-a

- --

-

Co -

_O

-- CD

W •)-

N

0'

0 0 W C.J c.j - -

Cb

18

1.6 S

I

2

S.

NACA RN L51G31

.8

S .L._ --I -

8

1W. HH ) 20 40 60 80 IC Percentcna Percent chord

(a) a, 11.0° ; 8 25.2°. : (b) a, 17.0° ; 8 31.9°.

o Convex surface o Concave surface

Lb

S..8

ii18, - 0 0 20 40 60 80 100

3.29-- I I

24---_

N S 1.6 - - -

.8------p.I H

0.t-T_I I U O 40 & 80 tOO 0 20 40 60 80 100 Fitent chord . Percent chord (e) a, = . 30.0 0 ; 8=43.50. L (f) a,= 36.00; 8=47.4°•

Figure l Li. Blade-surface pressure distributions and blade section characteristics forthé cascade combinat4on, = 3Q0, a and blade section, N4CA 6-(18)io.

Percent chord Percent- chord- .

(C) a 1 19.0 0 ; 9 = 338 0 (d) a = 24.0°; 8 z 38.6°.

0 3.2

S 1.6

.8

NACA RM L51G31

52 r- 1.1

48 1— i.c

44 I—.9

40 .8

deg— Cz

36 .7

32 .6

28 1— .5

24 i.— .4

20 L_ .3

90 .08

80. .07

70 .06

60 —1 .05 Icw

DCdj

50.04

0 —1 .03

30 —1 .02

T071=1 UO

l0 —J0 16 . 20 . 24 28 32 36

a1 , deg . .

(9) SectiOn characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure l ii. . - Concluded.. . . . .

1.6 -i

S .8

0

1.6

S .8

- 0

0 0 20 40 60 80 100 Percent chord . Percent chord

(C) a, : 4.O°; 9 = 3.4°. (d)a, z 6.0°; 9:540

3.2

Z4

S 1.6

.8

0

3.2----

24

S 1.6;

•:" 0 20 40 03 80 tOO

Fment chord (e) a,: 9.0°; 9:8.30.

Figure 15.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-010.

0 20 40 60 80 100 Percent chord

a,: 15.0 0 ; 9 = 13.84.

distributions and blade section Combinat1.n, 01 = 300, a = 1.505

50

NACA RN L51G31

2.4 /

1.6 .1.6

S

S

.8

0 Percent chord Percent chord

(a) a,: _3.00; 9 _390 (b) a, 2.0 0 ; 9 = 1.3°.

o Convex surface c Concave surface

MENEM MENEM MENEM

SEEMS .8

EMENEN MENEJ

NACA RM.L51G31

51

Cl,

_ MENNEN an ___ U.

MIMMEMENEEM

MEMEMMUSIEW

MWEEMEMENHMEMIMEMEMEN

ENEREEREME EREMEMEMENE p P0 PA, 0 ,AO

_N

20 i- .4

16F— .3

- .06

0 —1 .05

30 .-1 .04

L'c w.

CdI D &

10 —102

.0I

12 .2

0, deg C11

4 I— 0

II

-'10 -J 0 0 4 8 12 16

a,, deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading - edge roughness.

Figure 15.- Concluded.

II,

S

52. S

24

1.6 S

.8

N.ACA RML51G31

.8

1.6

S .8

0

1.6

S .8

0 0

'0 20 40 60 80 100 "0 20 40 60 80 bC Percent chord Percent chord

(a) a, a _5.00; 9 22°. (b) a1 : 1.00 ; 8 : 4.1°.

o Convex surface o Concave surfacp

Percent chord - - . Percent cho

(c) a 1 : 7.0°; 8 9.8 0. (d) a 1 : 9.00; 9: 12.00.

3.2

a4

S 1.6

.8

0

• 32

24

S 1.6

.8

0 20 40 6D 80 100 Frtent chord

(e) a, = 15.0°; 9 = 17.8°.

Figure 16.- Blade-surface pressure characteristics for the cascade and blade section, NPLCA 65-410.

0 20 40 60 80 100 Percent chord

a, = 21.0 0 ; 8z 22.60.

distributions and blade section combinat-ion, 01 = 300, a = 1.50,

NACA RN L51G31 -

dO

w j 0 0 0 OQO 0 0 0 I I I I I I I I I o 0 0 0 i 0 0 0

I I-I I I I-I I I I I I Icj

53

0 4-0

OU) U) w

c.c - C

fUP

IIIH:IIIjIiIr 0 N N N OD 0

S 1.6

.8

0

S 1.6

.8

(•1

714. NACA RN L51G31

1.6

S

.8

MMM 9109OWNE-760254

1.6

S

.8

I I I 1. 1 I ) 20 40 60 80 I(

Percent chord Percent chord (a) a,: 1.40 ; 9 :4•90• (b) a, 4.70; 8 11.0 °

o Convex surface Ii Concave surface

S

LE

S .E

Oti I I I I I 0 20 40 60 80 100

Percent chord (c) a,: 11.7 0 ; 8:18.4°.

H 0 20 40 60 80 IC

Percent chord (d) a, : I•3.7 0; 8 = 20.3°.

2.4

24

0 20 40 83 80 tOO Frcent chord

(e)a,:18.7°; 9:253°.

Figure 17.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-810.

0 20 40 60 80 100 Percent chord

a: 24.70; 9 30.50

distributions and-blade section combination, 01 = 30°,- 1.50,

U 0 0

'4-0V) &0

c 0'

0

ii 0

c 0'

.2 ' U '4-a, C',

a) ,-1

C.)

0

0

r-4

NACA RM L51G31 '5

co Wqt Cl - o o 0 0 o 0 0 Q o

I 1' I I I I I I I I I 1 o 0 0 0 0 0 0 0 In II) Cl -

-\ -- -- --

-\--

0

----- -

- -- CD

--

-

, - -

A-

W

I I I .1 I I I I: I ID o 04 co

04 04 -

4.

56

24— -

S

NACA RN L51G31

4

1.6

S

Percent chord - (c)a,:1640; 8=27.0°.

3.2

2.4

S 1.6

.8

0

VMS me 0 0 "MEME mm M- M- I[I

.8 .8

.0

0(

F'ercent chord Percent chord (a) a1 :8.10; 9:18.70. (b) a1 : 14.Io; 9: 25.0°.

o Convex surface o Concave surface

1.6

'S .8

S .8

Percent chord (d) a1 l9.I°; 8 =29.9°..

3.2--- ' I I

02040680I00•. Percent chord

(e)a1=25.I°; 0=35.7°.

Figure 18.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)

0 20 40 60 80100 Percent chord

r() a,=33.I°; 9:4280

distributions and blade section combinaion, 01 = 300 a = 1.50,

LO.

NACA RN L51G31

57

- '0 EJ I0 - - w

------

0

CD

ej

—

—.-

-2 F- w

I I

,ILI

1k k S?

co

co W — o o 0 0 0 Q 0

11111111 It IIII I o 0 0 0 0 0 0 / 0 0 C -

U 0

4-0

00 b.

C

ii' V

-

00 U

U.-

U,

0'

1.6

S .8

0 0

1.6

S .8

NACA RM L51G31

2.4

1.6

1.6 S

S

.8

o 20 40 60 80 100 20 40 60 80 Ic Percent chord Percent chord

(o)a,=12.0°; 9:2480 (b) a1 =17.0°; 8=30.5°. o Convex surface o Concave surface

Percent chord Percent chord (c) a, =19.00. 8=32.4°. (d)a,=2I.0°; 8=34:7°.

2.4

• S. 1.6

.8

0

3.2

21

S I.E

.8

0 20 40 OD 80 tOO Percent chord - - Percent chord

(e) a1= 27. Ô°; 8 40.6° r - T (f) a = 33.0°; 9= 46.0°.

Figure 19.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 300, ci = 1.50,

blade section, NACA 65-(1)10.

NACA RM L51G31

28 I— .5

24 .4

20L_.3 E - -

- a, deg

(9) Section characteristics*, arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 19.- Concluded.

- 12 16 10 - 24 28 32

o 8

2l

G Cd

A C1

- k - ---

/0,7

/ --_•7__ --

- 4 -- - \?<

- --- -

48 1.0

44 I— .9

40 F— . 8

36 .7

0)deg

32 1- .6

80-1 .07

70—I .06

60 —I .05

50-1.04 IC

LWI

I Cd, 40-H .03

30— .02

20— .01

tO— 0

1.6

S .8

- --

1.6

S . .8

0 D

NACA RM L51G31

2

1.6 I, S

S

.8 .8

0 rercen cnora Percent chord

(a) a,=12:o'; 0 = 28.1°. (b)a,:1800; 0=34.71

o Convex surface o Concave surface -

D rercenr cnora Percent chord (C) a1 =20.0°; 0 a 36.6°. (d)a,22.00;

3.2

2.4

S 1.6

.8

0

'020406080100,

!016'

24

S 1.6

.8

(•1

0 20408D 80100 Percent chord

(e) a=25;O°; 941.6°. 'TM• (f)

Figure" 20.- Blade-surface .pressre distributions characteristics for the cascade combinatiJ, and blade section, NACA 65-(18)io.

20 40 60 80 100 Percent chord

a1 : 31.00 ; 8=47.3°.

and blade section = 300 , = 1.50,

NkCA RN L51G31 61

48 1.0 - _________ - - - 60 /0'.06

0 9 - --o C,

---- -

_7-50—.05

• 441911t1 . • I/

40 .8 —4 40 .04 cw

' ______ a

36.7_ Z -------111130103

32 —.6 - 7 /

- —20— .02

281.5z1i

i771111,01•0I

.

24 - - 28. 32 0 0 a1 , deg

(g) Section teristics ; arrow shows characteristics; design angle of attack;

roughness.flagged symbol edge nbol indicates leading-

Figure 20.- Concluded.

sMEN •Frcent chord

(b) 1 3.80 , 91134°

o Convex surface t Concave surface - - - - -

1.6 bne

S .8 E OK I I I I I 0 20 40 60 80 100

Percent chord.

(d) a,77°; 8=6.2°

62 NACA IUt L51G31

2A

1.6 1.6

S

S

1.6

S .8

.8

0

m m -maqi1mil-mmM1101 Percent chord

(C) a,5.8°; 8=5.00

•---I

Percent chord

8110.50.

I --- 3.2-- I

Z4 2

.8 = =-i - . 8 -a--

0.i—I—i

0 1111

0 20 40 83 80 100 0 20 40 60 80 100 Rercent chord . . . Percent chord

(e) a, = 1140; 8=8.60. L (f) a,15.60; 8=10.3°.

Figure 21.- Blade-surface pressure di stributAong and blade section characteristics for the cascade combinatn, Ol = = 0.50, and blade section, NACA 65-J41o.

0) deg li

0k— .4

50 -H .04

LICw

C dl .03

NACA RN L51G31

63

16 p .8

12 F— .7

8 I— .6

I I o 8

o C11

G Cd1

CwI

L D

80 .07

60 -H .05

4 f---..3

30 - .02

- 8F--- .2

0 —1 .01

10 I 0 0 4 8 12 16

a,, deg

(9) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading ,- edge roughness

Figure 21.- Coided.

12L__ I

I.E

S .8

0

t-'ercent chord (C) a,'7.3°; 99.7°

LE

S .8

0

Percent chord (d) a,9.30 ; 9I14°.

a'2

NACA EM L51G31

2.'

1.6

S

0 20 40 60 80 Percent chd I-rcejj chord o Convex surface (0) a, 1.5°; 0-5.6! Concave surface (b) a,-5.4 0 , 8 -8.V

6.

2

1.6

S

S 1.6 S 1.6

0

440 20 40 60 80 Percent chord

100 0 20 40 60 80 100 (e) a,' 13.30 ; 9 '14.3°

Percent chord a,' 17.4°; 9' 162°

Figure 22.- characteristics

B1ade_5face for the

pressure distributions and b1ae section and blade section, NACA

cascade combination 65-(12)10. i = = 0.50,

NACA RM L51G31

3 r 1.2

32 I— 1.1

28 h— 1.0

24 .9

de[_- cz 20—.8

16 .7

I2—.6

8F—.5

4 L_

65

90— .08

80— .07

70— .06

60 __J .05

LIC. I

D1c I

50 _4 .o'

;o __I 03

50 __ .02

0 10

0. C11

-: :::-

-

1

Ar iii J

ki V D 4 T8 12 16 90

a/. deg

(g) Section characteristics; arrow shows design angle of attack.

Figure 22.- Concluded.

S 1.6

' .8

0

S 1.6

.8

C)

66

NACA RM L51G31

I

1.6 1.6 S S

.8 .8

OC Percent chord Percent chord

(Q) a, 4.8°; 8-10.4°.0 Convex surface 0 Concave surface (b) a,08.7*', 9-14.3°

1.6

S .8 8 I—

0)

Percent chord

Percent chord (C) a,I2.70; 9I7I°. (d) a1 = 14.60; 8-18.5°

3.2

P-4 24

0 20 40 63 80 100 0 20 40 60 80 100 Percent chord Percent chord

(e) a,19.7 0 ; 9-21.3 )a,B2I.70 9BI84o

Figure-23.- Blade-surface pressure distributions and blade section characteristics for the cacadecombinat.on, Ol = 0.50, and blade section, NACA 65-(18)io.

) —i .08

—1 .07

)_1.06

) —1 .05 Icwi

-Ha Ic i d1

—1 .04

- .02

NACA RM L51G31 67

24 H 12

8de4__ cii

20 1.1

36

28F-- 1.3

32 1.— l.

16 l— 1.0

2 1— .9

I I

0 8

- a C11

A

-

-

/Z25

9

_G CdI ir

- -1--

--

I Yin - 61

L C

8 I— .8

4.7

a1,16 20 24

deg

(g) Section . characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 23-- Concluded.

8 12 -

1.6 S

68 NACA RM L51G31

.8

MMMMMI

0 (0) a,=O.Oo. 6=1.0 Convex surfaceci Concave surface(b) a,4.20

Lb

S .8

1.6

S .8

0 20 40 60 80 tOO 0 20 40 60 80 tOO

Percent chord Percent chord

(C) a, = 6.30 , 8=5.9° (d) a,10.00 6=9.3°.

a4

S 1.6

24

S 1.6

.8

0O 20400 80 100

Frtent chord () a,140 0 , 0=12 .6 0. .

Figure 24.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-410.

0 20 40 60 80 100 Percent chord

(f) a,20.0 0; 6=15.810

distributions and blade section combination, 0 1 450, a = 0.75,

NACA RM L51G31

69

28

24 I— .6

20 1— .5

9, deg - C11

12 - .3

8—.2

ole

o Ci,

Cd I /

i

i

_ c

50 – 1 .07

;o —1 .06

50 —1 .05

to —104

L

d1 0 H•°

0

4 I— .1 [I.— fIJ

F . I. 0 L_ 0 I_ 20 0

0 4 8 12 16 20 a,, deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 211.- Concluded.

70

NACA RM L51G3i.

• 1', c 4

1.6

6 S

S

.8

B IF-I

20 40 60 80 100 20 40 60 80 100 Percent chord

Convex surface Percent chord (0) a,= 34°; 8=a5° Concave surface (b) a, 75°; 9 12.5°

Tc -^ >-^ I - -I

o-____ 0

K— 0 20 40 60 80 0 0 20 40 60 80 100

Percent chord Percent chord

(C) a,9.4°; 8 14.4° (d) a,II.50 ; 816.1°

3 .2 -

2.4

S 1.6

.8

0

3.2---

S 1.6 -

24__:__

I

-

- - -

-0— -P

020406380100 Percent chord

(e) a,-15.40 ; 0- 19' .6't . (f)

Figure 25.- Blade-surface pressure distribution characteristics for the cascade comb1nati, and blade section, NACA 65-(12)10

20 40 60 80 100 Percent. chord

a,- 195*,' 9=22.7?

s and blade section Ol = 50 ' = 0.75,

NACA RN L51G31 71

32 r- 1.1

28 h— 1.0

24 F— .9

20 .8

0, deg[-

16 I-- .

2 I— .6

8 F— .5

4 I— .4

- A - I I I I

C', ( -p----/ - - - - -

Z7

iIIIIIiIII

30 - .03

20 - .02

- .01

50 —1 .05 ICwi

DCdl

40 —I .04

60 —I .06

80 —1 .08

—JO 0 4 8 12 16 20 24

a1 , deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 25.- Concluded.

72

N.ACA RN L51G31

.1.e

24

2.4

1.6

1.6 S

S

.8 .8

0

0 Percent chord .rcerfl chord -

surf ace(0) a1 = 7.0°; 8=I4.5° e ib) a,.1 1.00; 8=20.3°

1.6

1.6

S .8

S .8

0 20 40 60 80 100 Percent chord

TTL 0

Percent chord - JO

(C) a, = 14.00; 823.3°

(d) a,16.00 , 825.0°.

3.2

3.2--

--w a4

24 - - - -

-----S 1.6

S 1.6--—_--_-

.8 .8— --

-e-

00 20 40 8D 80 100

Percent chord

0 20 40 60 80 100 Percent chord

(e) a,21.00 ; 8=28.60. jf• ) 61 = 24.00 ; 9=29.2°

Figure 26.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, Ol = 45°, a = 0.75, and blade section, NASA 67-(18) LO.

70 .06

60 —I .05

50 —I .04

L I D_lCa

d1 40 —I .03

30 ---1-02

0-H.0l

NACA F.M L51G31 73

32 1.2

2$ 1.1

24 1.0

8, deg— CZj

20 .9

16 F— .8

2 H

8L_ .61 I I I I

4 8 12 16 20 24

a,, deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 26.- Concluded.'

1.6 S

.8

1/ I . I I I I

74

N.ACA RM L51G31

o 20 40 60 80 100 "0 20 40 60 80 100 Percent chord Percent chord

(a) a1 3.00; 8 = - 5.00. (b) a1 3.00; 8 = 1.3°.

o Convex surface r Concave surface

1.6

S .8

1.6

S .8

5

0

Iercent chord Percent chord

(C) a6.O°, 8 : 3.80. (d)a,9.00,O:620

3.2

P-4

S 1.6

.8

0

3.2-- I I S

-- . S

24.

S 1.6 ----

r) L 0 20 40 80 80 100 0 20 40 60 80 100

Percent chord Percent chord ce a =12.0°; 8 9.40. ç (f)a= 15.0 0; 8:117°

Figure 27.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, Ol = 50 .' 1.00, and blade section, NACA 65-010. 5

WTV

NACA RM L51G31 - 75

-- -j

D .08

D .07

D .06

D .05 C

a Cd1

D .04

D .03

0 .02

0 .01

0 0

9 . 9

9.

a,, deg

(g) Section characteristics, arrow shows design angle of attack.

Figure 27.- Concluded. 9 9

.3

24 .4

• 20° .3

$6 .2

•12 .1

8, deg— Ci

80

4 -I

0

-4

-8

76

NACA RM L51G31

' .-t

2.4

4 1.6

1.6

S

S

.8 .8

mm--

'ercent chord Percent chord

(a)a,:I.O°, 8=3.30 (b)aj=5.O°; 6=7.30.

o Convex surface o Concave surface

I .Q

S .8

1.6

- S .8

0

Percent chord Percent chord

(C) a1 7.0°; 8 = 8.6° (d) a, =11.00; 8= I2.I°

3.2

a4

S 1.6

.8

0o 20 40 83 80 tOO .0 20 40 60 80 100

Percent chord Percent chord (e)ajI4.0°,8=I4.5° c (f) a 195°; 6=17.30.

Figure 28.- Blade-surface pressure distributions and blade section characteristics for the cascade combintion, 01 = 450, a = 1.00, and blade section, NACA 65-41o.

24

S 1.6

.8

0-1 .04

0— .03 c.wI

-Ha Icdl 0— .02

NACA RN L51G31 77

20 .6 • 0—i .05

0 9 - - nczI

— G Cd1—___----—_-.__---7------,4 4

CW:. 777\ -_

3

_ ,PØX(

16 F— .5

12 .4

9, deg—Czi

8-3

4 I— .2

0—I.oi

0 4 8 12 16 20 a,, deg

(g) Section characteristics; arrow shows design angle of attack.

Figure 28.- Concluded.

. .. 0_J0

Em

"a...'

MEN a

78

S

-r 2

S

NACA RM L51G31

I..-.'

NoIIII I AV 2 sq.. 0

iIRiIal' .80 m

t-'ercenT ctlord Percent chord (a) ap5.7°; 8 107o (b)a17.7°; 0=12.70.;

o Convex surface D Concave surface

10 Percent cnora Percent chord

(C) a1 =9.70; 9:f4•40 d)a1=I3.7°; 8=18.0°.

3.2----------- 3.2' i' I

H-----

2.4 - - - - - 24 - - - -

S 1.6 ---- S 1.6------------

OH i I 1 0 020408J80100 020406080100

Frcent chord Percent chord

(ea,=I8.7°; 0=20.9°. CL (f) a1 =22.7 0 ; 8=21.3°.

Figure 29.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, = 450, a = 1.00, and blade section, NACA 65-810.

LE

S .8

D0

------ 0 Cl, — - -

G C1 - •0

A owl

X^ 000000,.;0000l^

-

--/7--\

79

80 o.08

70.07

60 .06

50 .05

40 .-1 .004 IC

L II

a

I Cd, 30 -1 .03

NACA RM L51G31

28 1— .9

24 F— .8

20 I— .7

16 I- .6

.6, deg__ C11

l2I-.5

8—.4

4 —.3

ri-9

20H .02

10 01

0 0 8 12 16 20 24

deg 0

(g) Section characteristics; arrow shows design angle of attack.

Figure 29.- Concluded.

C

.8

0

.8

0JO

Percent chord • Percent chord (a) a,:_0.90 ; 9=4.10. (b) a,=5.I0;

o Convex surface Concave surface

80 S NACA RN L51G31

1.6

LE S

S

1.6 -

S .8

o—

1.6

S .8

0

- - -

—p

_--__u u 'iu bU 80 DO 0 20 40 60 80 100

Percent chord Percent chord (C) a,=12.I 0 ; 9 : 196° (d) a, : 16J 0; 8=2330

- 3.99

S I

3.2--IS

SL6 ---

PS

0 20, 40 SD 80 tOO Fitenf chord

(e) a, : 211 0; 8=2630 IM Figure 30.- Blade-surface pressure

characteristics for the cascade and blade section, NACA 65412)

'o 20 40 60 80 100 Percent chord

MWIF (f) a, = 25.I1 9:2590

distributions and blade section t combination, 13i = 1..5o , a =1.00,

LO.

NACA RN L1G31

81

o o 0 q0 oo - a o

I I I_ I I I I I I I I I I I I o o 0 0 _jIo 0 0

2qt in NN

U 0

Q c3•o'j_4o

0 aOl 4

N

•1-0

o N 0

01

0)

• (0

InH

CY 0 - - 0 -. L.

o-

In

CD

I F-

I

(0

I I I

10

I I I

-

I I I

0'

I (0 N N

0 N -

(0 N -

(0 1 0

LE

I MW I

1

IMME 01

I

^ 0 . rel Wrew,

.8

Ii, ) 20 40 60 go i

82 NACA RN L51G31

24

1.6

1.6 S

S

Percent chord Percent chord (a) a, = 7.0°; 8=16.6° (b) a,=I1.00; 8=20.9°

0 Convex surface J Concave surface

1. CV.V,-e - - - 1.6

L_- - -

S .8__ ___ S .8---

0 - - ----

- - -

-

- 0

--

- -

-

- 0 20 40 60 80 K 0 0 20 40 60 80 100

• Percent chord Percent chord (C) a, = 15.0°, 9= 25.1°. (d) a,=17.0 0; 926.6

Z4

S 1.6

.8

0

24

S LE

.8

00 20 40 6D 80 100

- - - Percent chord Percent chord

(e) a,21.0 0; 9=30.0° T ,(f) a,=27.00; 8=32.40.

Figure 31.- Blade-surface pressure distributions and blade section characteristics for the cascade combinat1n, = 5

0 = 1.00, and blade section, NACA 65-(15)10.

- 11

NACA RN L1G31

83

36 F— I

28b•

8, deg - C

24—.

20 I-

16

12

. :—MENOMONEE

H. MMUMMUNRM lU

CWI

MERNME I MEM MEMENEEMEMEM MEMMENHEMEME EMEMEMEMEMEN

MMRMEMMMMM MIMU •EffiffiMEMMEMMME ONEMMUMEMMMM MMEMIMEMMMMMM

I

70--i.06

.05

50—I .04

CdI 40—I .03

.02

20—I I

lO— 0 4 8 12 16 20 24 28 a1 , deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 31.- Concluded.

-----I

1.6

s .-

- 1.6 S

.8

814.NACA RM L51G31

2

I-'ercent chord Percent chord (a) a,=9.00, 0=17.9° (b) a,=13.0 0, 8=24.3°.

o Convex surface Concave surface

1.6

S .8

• 1.6

S .8

0

Percent chord (C) a,17.00; 8=28.5°

3.2

2.4

0 20 40 60 80 100

ACA

S 1.6

.8

0

0' 1 I I I 0 20 40 60 80 100

Percent chord (d) a1 z 19.0°; 0=30.4°.

3.2

24

S 1.6

0 20 40 60 80 100 Percent chord

1. f) a1 =26.00 0=33.8°

distributions and blade section comb±Mion, l = 45°, a = 1.00,

LO.

Frtent chord

(e) a,=23.0°; 0=33.2°

Figure 32.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(18)

NACA RM L51G31

85

40 12

36 - I.;

32 I— 1.0

28 .9

Odeg H 1

24 - .8

20 I— .7

I6— .6

12 1..

D

0 Odl A Cw1

11 b I •_

A\ Y I/A/ -------

47811;16 20 24 21

70 •—i .07

60 —1 .06

50 ---j.05

40 —104 I C w,

D If' I 'di

30 —I .03

20 --j.02

[I.— LI

0 JO

a/ , deg

(g) Section characteristics; arrow shows design angle of attack.

Figure 32.- Concluded.

WANACA RM L51G31

-------

2.4

-o1.6 1.6

S

.8

C)

.8

0 20 40 60 80 tOO 00 20 40 60 80 Percent chord Percent chord

(a) a, = 15.O°; 8=28.2° (b) a1 =18.0°; 9=31.5°

0 Convex surface ° Concave surface

S

0 20 40 60 80 100 ' 0 20 40 60 80 100 Percent chord Percent chord

(C) a1 = 19.5 0; 8= 33.0 (d) a1 210°; 834.30

3.2 - - - 3.2 - I I

2-4 - - - 24 - - -

ri

S 1.6 ----- -- S 1.6— - --

PIN '-T-U-i I-EK

------

0 __________ 0------0 20 40 &) 80 tOO 0 20 40 60 80 tOO

Frcent chord Percent chord

(e) a,=24.0°; 8=370°. - - (f) a,3Q0°; 840.5

Figure 33.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 450

.9 = 1.00,

and blade section, NACA 65-(2l)10.-t.

1.6

S .8

0

NACA RM L51G31 87

90

30 .08

70 .07

0 .06

0 .05 cw

L a'CdI

0 .04

10 o

0 .02

0 .01

0 ...o 12 16 20 24 28 32 36

a, deg

(9) Section characteristics; arrow shows design angle of attack.

Figure 33.- Concluded.

48 1.3

44 1.2

40 1.1

36 1.0

8, deg C11

32 .9

28 .8

24 .7

20 .6

16 .5

ma

88

NACA RN L51G31

2.4

1.6

1.6

S

S

.8 .8

0 20 40 60 80 tOO 00 20 40 60 80 100 Percent chord Percent chord

(a) a1 = 16.0°; 8 = 30.4° (b) a, : 20.00; 9:355°

o Convex surface a Concave surface

•i

S

S ,8 I-

0 20 40 60 80 100 Percent chord

(C) a, = 24.00; 9:39.50•

3.

2

01TT 0 20 40 60 80 100

Percent chord (d) a, = 200; 9=40.91

24

S I. S 1.6

.8

0O 20 40 60 80 100

Percent chord (e) a1= 30.00; 8=42.4°.

Figure 34. - Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(24)

0 20 40 60 80 100 Percent chord

_____- (f) a,=34.00; 8=43.20:

distributions and blade section combinon, f l = 450 , a = 1.00,

LO.

NACA R1'1 L51G31

89

48 — 3.3

44 - I.?

40 . 1.1

36 - 3.0

9 1 deg — C11

32—.9

I I, 0 8

C

G Gd1

.Gw1

--

80—i .07

70 .06

60 05

50— .04 I

LCw

Dd1

40—.03

281— .8

30 .02

24 - .7

20 .03

20 L_ .632

31 10 10

a1 , deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 34. - Concluded.

S I.

Percent chord - (C) a, : 25.0°; 94I.4°

3.2

Z4

- - - -,NACA RN L51G31

- -- _

Z.Aq

1.6

1,6 S

S

.8

00 20 40 60 80 100 20 40 60 80 100

Percent chord Percent chord (a) a, = r?5°; 9 : 31.60 (b) a1 = 21.0 0; 9=3I0.

0 Convex surface

m (nnnuø enrftia. - . •i U 1O

1.6

•.

S .8

S

0o 20 40 60 80 100

Percent chord (d) a, = 20 0; 9:4340

3.2

24

S LE

______ -----

. _ 0204080100 020406080100

Percent chord Percent chord (e) a, 29.0-; 9=443o• f) a/ = _33.0o; 9 = 4550

Figure 35.- Blade-surface pressure distributions and blade section characteristics for the cascade combinatio, Di = 450 , = 1.00 and blade section, NACA 65-(27)10.

NACA EM L51G31

60—1 .05 ICw

LI'

C1 50—.04

60 '.3

56 4

52 1.3

48 1.2

8, deg— Cl1

44 II

40 1.0

36 .9

91

90--.08

80—.07

70 ­1.06

32 .8

28 .7

• 9___________________

:. R _ A

CW1. ---ILl •1 11

EMEMEMEMME_

EMEMEMEMME lit

EMEMENNORE MOMOMMEMME EMEENUMMOM_MMUEMMEEMM_

EMMEMEEMEM MOMMEMEMEM _ .11

MIMEMEME

O —1 .03

30—I .02

20—.01

--

10—n 16 20 24 28 32 36'

a1 , deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge , roughness.

Figure 35.- Concluded.

-1

92

NACA RM L51G31

24

1.6

1.6 S

S

.8 .8

o 20 40 60 80 100 "O 20 40 60 80 100 Percent chord Percent chord

(a) a,=I.0°; 930e (b) a 1 = '7.0°; 8=8.4°. o Convex surf ace. a Concave surface

1.6

S .8

00. 20 40 60 80 100 0 2P 40 60 80 100

Percent chord Percent chord

(c) a,, = 9.0° ; 6= 10.5°. (d) a, = 13.0°; 6 = 14.5°.

3.2

a4

S 1.6

.8

0

1.6

S .8

24

S 1.6

.8

0 20 40 &) 80 100 Frcent chord

(e) a, = 17.0°;817.5°. c

Figure 36.- Blade-surface pressure characteristics for the cascade and blade section, NACJ 65-410.

• 0 20 40 60 80 tOO Percent chord

(f)a,=22.0°;620.7°.

distributions and blade section combination, 45°, a L25,

93

60 .06

50 .05

40 .04 IcwI

k—la D

Cdl 30— .03

ao —H .02

24 __.6

20 L—.5

6 I- •

deg Cj

2 1- .

8 I.— .2

o 8

o C11

__..._G C1

A Cw1

;p7 -

I ---- -Z 6L -

, 114

28 r- 70--1 .07

- - .1

ii.II

—J 0 4 8 ,12 16 20 24

o o

(z,, deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 36.- Concluded.

9k.. NACA RN L51G31

4

1.6

6 S

S

.8

n0 20 40 60 80 tOO

Percent chord Percent chord (a) a 1 = 7. 1 0 ; 8=5 . 0. (b) a = 12.6°; 8=20.9°.

o Convex surface El Concave surface

1.6

S .8

00 20 40 60 80 100 0 20 40 60 80 tOO

Percent chord Percent chord (C) a 1 = 15.10; 8=23.4°. (d) a 1 18.1 ° ; 8 26.10.

3.84

3.2

2.4

S 1.6

.8

0

LE

S .8

C)

24

CA

S 1.6

----

0 - p

(P0 20 40 & 80 tOO

Percent chord

(e)a, 24 . 1 0 ;9= 31.40.

Figure 37.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)

0 20 40 60 80 100 Percent chord

(f) a, = 30.10;8=32.10.

distributions and blade section combination, Ol = 450 , = 1.25,

LO.

36

32

28

0 deg-

20L-

16

2

8

4

Cd

1_

i• u•uiu:

m

MEMOMMEMEMEMEM MEMEMEMEMENEWEII/M MEMEMEMEMEMEME MEMOMMEMEEMEME MEEMEMEMEMEMME MEMEMEMEMEEMMM

• MOMMEMEMEMEMEN EMEMMOMEMEMEME MEMEMEMMUMENEW

NACA RN L51G31 - 95

80• —r .08

70 .07

60 .06

50— .05

k—la D

40_j .04

0

30 .03

20 .02

10 .01

0 0

a, deg

(g) Section characteristics, arrow shows design angle of attack; flagged syynbol indicates leading-edge roughness.

Figure 37.- Concluded.

96

NACA RM L51G31

24 2.4

1.6 1.6

S S

.8

U Zu 'v 60 ENO w 0 20 40 60 80 100 Percent chord .rcent chord

(o)a, = Il.00 ;8=235 0 (b)a,=16.O°;9:287 0 Convex surface El Concave surface

Lb

g S• .8

S .8

0

0

.8

0 -n nn Aflaaa . 0

Percent chord (C) a 1 = 18.0°;9=30.7°.

o 20 40 60 80 100 Percent chord

(d)a,=200° ;8=33.10.

- - -- 32

2.4------- 24 -

S 1.6—------- S 1.6-

----

.8---- .8-----

0 - - - I 0 i- - - - 020406380100 020406080

- 100

Percent chord Percent chord (f) a, 35.0°;9=425°. C (e) a L = 26.0°,9 : 38 . 00 .

Figure 38.- Blade-surface pressure distributjons

-

and blade section characteristics for the cascade combination, j = 450 , a = 1.25, and blade section, NACA 65-(18)io.

52 - 12

48 I— Ii

44 I— 1.0

40 1— .9

.8

O) deg — c11

32 .7

28 1— .6

24 I— .5

20 .4

16 3

0 8

a C21

Gd 1

.6

--GA

-----

- 7 -

-

/

7_ -

o

-

-

-- :—Z---1- -- - -- -

NACA RM L1G31 Ji*- 97

50—I .05 C

L .1

40__1 .04

30--I.03

.09

.08

.07

.06

20_1 .02

10 .01

0 0 8 12 16 20 24 . 28 32 36

a,, deg

(9) Section characteristics . ; arrow shows design angle of attack flagged symbol indicates leading-edge roughness.

Figure 38.- Concluded.

Co_ -.

98

1rAL

NACA RN L51G31

• 2.4

1.6

1.6 S.

S

.8 .8

0 20 40 60 80 100 "0 20 40 60 80 100 Percent chord Percent chord

(a ) a 1 0.0°; 9=_I5 0 . (b) a 1.: 2 .0 0 ; 9 0.5°.

o Convex surface O Concave curfnra

Percent chord Percent chord L Nu1111 .10

(c) a 1 = 5.0°; 8 3.8 0. (d) a 1 8.0°; 9:660

3.2 -- 32

2.4

24--

S 1.6

S 1.6

.8

00 2040 60 80 100

0. 20 40 . 60 80 100 Frcent chord

Percent chord (e) a,=lI.0° 1 0=9.4 0. 0

](f).a,=I7O0; 9=14.7°.

Figure 39.- Blade-surface pressure distributions and blade section characteristics for the cascade combjhation, l = 450, a = 1.50, and blade section, NACA 65-010.

D

Lb

S .8

S

.02

0 .01

- i 0

a/ , deg

(g) Section characteristics ; arrow shows design angle of attack, flagged symbol indicates leading-edge roughness.

Figure 39.- Concluded.

4 0

0 -I

- 4 -.

NACA RN L51G31

99

2 —.4 50 —, .06

40 .05

30 .04 cw

a'

20. .03

0 9_

0 Cl,

16 I— .3 o Gd 1 -

A Cw,_

0 12 .2

U,degHCz

8—.l

1.6 S

.8

0

LE S

100 T&L

NACA EM L51G31

2

0 20 40 60 80 100 "0 20 40 60 80 100 Percent chord Percent chord

(a) a,=-3.0 8= -2.O o. (b) a 1 = 3.O°; 85.54

0 Convex surface I I I I ° Concave surface

Lb

S .8 S .8

0 0D 20 40 60 80 100

Percent chord (c) a, = 8.0 0, 9= 10.4°

0 20 40 60 80 100 Percent chord

(d) a,=lO.O°,

24

S 1.6 I.6----

L/ CL/ '+U W i(.) IL).'

Percent chord (e) a1 = 16.0 6 , 8=17.9°.

Figure 40.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-4io.

0 20 40 60 80 100 Percent chord

a1 = 22.0 0 , 9=22.1°

distributions and blade section combijtion, 01 = 450, a 1.50,

101 NACA RM L51G31

- .07

0 .— .06

-0 - .05

24 -

20--

l6 -

12 -

8, deg

8--

4-

0-

-4 -

0 9 o C11

.4-- G Cd1---.A

7/ IZ

- ---

-I - - -2

7 -- --- - - 0

tzz

2-1 I

0 4 8 12 16 20 24

'0 —1 .04 ICW

L I - a Dc

0 —1 .03

0 - .02

0 - .01

0_

a1 , deg

(9) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 40.- Concluded.

CON .

102 NACA RM L51G31

1.6 1.6

S S

.8

0 20 40 60 80 100 00 .20 40 60 80 100 Percent chord Frcent chord

(a) a1 = - 0.40, 9=5.2° ' (b) a1 5.7°, 8:11.7°

o Convex Surface

.8

0

1.6

S .8

1.6

S .8

0 I I I I 0 20 40 60 80 100

Percent chord (d) a, : 1I.7 0, 8:17.8°.

NACA

24.--

S 1.6:

I. 0 20 40 60 80 100

Percent chord (e) a 1 =16.70, 8=22.5 o C1

Figure 41. - Blade-surface pressure characteristics for the cascade and blade section, NACA 65-810.

0. 1 0 20 40 60 80 100

Percent chord (C) a1 =9.7°, 9:15.70

2.4

S 1.6

.8

0 20 406080 tOO Percent chord

-(f) ag: 25.7°, 9=28.6

distributions and blade section combination, i = 45, 1.50,

NACA RM L51G31 ..

N — 0 0 0 dS JO 00 Q 0 III lIIII•IIIl1

p

103

C- - ° ° 0 O 0 0

coi

OD

---- -7

---T---- ------7------

- --.--- - -

co— ç c j 43- -- __- ___ s 0

CY

—o o

____ ----F- (0 It) 1 N

C, a .-

00 0

—

00

0 '-4 •0

C.)

CP co C o

r

00 0 1)

00 U

LE•H

• 0 0 - 4-

0 > U)

0 -C

CP

— .4- o ' (0

U)

7.

(0

col

OX

a4

S 1.6

.8

0

24

S 1.6

.8

iOi. NACA RN L51G31

2A

1.6

S

.8

1.6

S

.8

()0 20 40 60 80 100

Percent chord (a) a, = 5.I 0 , 8=13.9°

20 40 60 80 100 Percent chord

(b) a,=12J°; 8:2140

1.6

S .8

0

1.6

S .8

0 0 20 40 60 80 100

Percent -chord (C) a,=16.I0 8=25.50

0 20 40 60 80 100 Percent chord

(d) a,=18J 0 ; 9=2730

0 20 40 83 80 100 020 40 60 80 100 Fttent chord Percent chord

(e) a, :22J 0 ; 8 :30.6? (1) a,276*; 9=35.0o

Figure 42.- Blade-surface pressure distributions and blade section characteristics for the cascade combinatio, = 450 , a = 1.50, and blade section, NPkCA 65-(12)10.

I _

CIQ 7IIIII -4

• co cjQ Q JO-----

-o oGI 4--------'----

-----a

a 0 4-0

.4-ou, U, 0

00

C

U)

.00

0) ) (#c d

. 0 0 Q(flQ)

- 0 0

_oU) I P4 4- (J

a

NACA BN L51G31

w o 0 0 qu coo Q0 111111 II Ill o 0 0 -ilo 2 10

105

IIIIIIIIIIIII Cd 0 (0 Cd

10 10 Cd N N - -

Co

NACA RN L51G31

2.4

106

24

1.6 S

8

n

1.6

S

.8

0 01 I I I I I 0 20 40 60 80 100

Percent chord (d) a,=20.0; 8:32.6°.

ri Percent chord

(C) a, = 18.00 1 8:30.5°.

S 1.6

.8

0

S I.E

(1

o 20 40 60 80 ioo JQ 20 40 60 80 100

Percent chord Percent chord (a) a,: 10.0°; 8=21.9° (b) a,=I6.0°; 8=28.2°.

0 Convex surface Concave surface

1.6

1.6

S .8

S .8

2.4

2

0 20406D 80 tOO -- - Frcent chord Percent chord

(e) a, = 26.0°, 8 :375 0 1 (f) a, = 32.00', 9:4090

Figure 43.- Blade-surface pressure disztbutions and blade section characteristics for the cascade combnation, i = 5

o ' = 1.50,

and blade section, NACA 65-(15)10.

NACA RM L51G31

107

.07

.06

.05

.04 C

a Cd1

.03

.02

.01

0

8 12 16 20 24 28 32 a, deg

(g) Section characteristics; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness.

Figure 43._ Concluded.

44 1.0

40 .9

36 .8

32 .7

deg CR

28 .6

24 .5

20 ..

108

iAL

NACA RM L51G31

2.4

1.6 S

.8

.—-wjo-

1.6

S

.8

11 I ) 20 40 60 80 IC

Percent chord Percent chord (a) a, = 14.00; 8=28.7 6 (b) a=I9.0°; 8=33.80.

o Convex surface O Coneava QIjrfn^_

1.6

£ S .8

1.6

S .8

(.)I I I I I I 01 1 1 I 1 I 0 20 40 60. 80 100 0 20 40 60 80 100

Percent chord Percent chord (c a, = 21.0°; 8=357 (d) a, = 24.0 0 8=38.41.

3.2

a4

S 1.6

.8

0

32

24

S 1.6

.8

C-)

0 204O80 too Frcent chord

(e) a,= 30.00; 8=43.60.

Figure 44. - Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(18)

O 20 40 60 80 100 Percent chord _______

______ (f) a1= 36.0°; 0= 47.8°

distributions and blade section combination ., 131 = 450, Cl = 1.50,

LO.

NACA RM L51G3 1 . ________________ 109

48 1.0

44 I— .9

40 I— .8

36 H • deg — Cl1

32L- .6

28 1— .5

24 I— •

20 1 .

- _L*C21

0d1/

cWI

--

/

-

-1-----7 ----- ----

- - __j _ -.----/

-

a- - -ia----

70- .07

60— .06

50— .05

40— .04 C WI

D Cd, 30— .03

ao— .02

10— .01

0— 0 )

a, deg

(9) Section characteristics; arrow shows design angle of attack, flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 44. - Concluded.

-.-

110

24-

1.6

S.

.8 .8

NACA RN L51G31

I /

0 20 40 60 80 100 0 20 40 60 80 100 Percent chard' Percent chord (a) a = I4.00 ; 82a1° (b) a,:20.OD; 936.8°.

o Convex surface Concave Surface

1.6

S .8

0 D

(C)rercenT chord

a,: 240 0; 941.1 0 (d)Percent chord

a,=27.0° 8=4410.

3.2-------I I

CA

24 - -

S 1.6—--- S

----

.8---

o.L - - - 0 0 20 40 6D . 80 100 0 20 40 60 80 100

Frcent chord . Percent chord Is) a1: 33.0 0 ; 8=48.70. . (f) a1=390 0 ; 9=5I.6o

Figure 45.- Blade-surface pressure di stributions and blade section Characteristics for the cascade combig jon, Ol = 450, and blade section, NACA 65-(21)10.

1.6

S .8

00

NACA RM L51G31 111

-- I I o 9

D C21

Cd,

.A C1---

---s

-H- 7_

-T61

-

--

------

--

//

-

-

--

---i

---51

- --

\\-

__L____ •A24J—.3

12 16 20 24.. 28 32 36 40 a1 , deg

(g) Section characteristics; arrow shows design angle_ of attack; flagged symbol indicates leading-edge roughness.

Figure 45.- Concluded. .

56 1.1

52 F— 1.0

48 F— .9

44 F— .8

40 - .7

9, deg —_

36 I- .6

-.be

—1 .07

-'--1 .06

—1 .05

- 04 C

H a

CdI —1 .03

—1 .02

—I ri

32 }- .5

28 , l­­ A

MEMEN MENii PO 4• .1 :.

112

NACA RM L1G31

2

1.6

S

S

.8

.8

0

Percent chord Percent chord (a) %= .16.0 0i 9 = 31.59. (b) a,: 2 2.0°; 8=41.3°.

o Convex surface rj rnwnwa mirfn.-a

1.6

S .8

S

Percent chord Percent chord (c) a,: 270 0 , 9=46.9! (d) v29.0 0; 9:48.7?

2.4

S 1.6

.8

0

24

S 1.6

.8

0 o 20 40 8D 80 100

Frtent chord (e) c,=35.0 0 ; 8=52.9°. CU

Figure 146. Blade-surface pressure characteristics for the cascade and blade section, NPLCA 65-(24)

0 20 40 60 80 100 Percent chord

(f) a,41.60, 0:579?

distributions and blade section combination, Ol = 450

y a = 1.50, LO.

NACA RM L51G31 . 113

68

64 -

60 -

56

52 - 1.0

8, deg —C1

48 - .9

44-8

40 - .7

36 - .6

32 —.5

28 -

- 0 9 - -

Cl,_

-

-

G Cd1-

-- Cwl-- -

-- --

. -

-

—

—

---

--

Vh^

L NACA

2-- 16 267 26 32 36

__

40

100— .10

90 - .09

80 - .08

70 - .07

60 - .06 cw

D ,.

d1 50 - .05

40 - .04

30 - .03

eo—.o2

10 - JDI

- 0

a1 , deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicotes leading-edge roughness.

Figure 46.- Concluded.

lb

S .8

-------- jUHUUVt surTuce

1.6

S .8

0

- 2.4

S 1.6

.8

0

24

S 1.6

.8

n

1114. C( NACA RN L51G31

2.4

1.6

1.6

S

S

.8 .8

Percent chord

(a) a1 0.2°; 9=0.4!

o Convex surface

20 40 60 80 100 Percent chord

(b) a1 2.I°; 9'19°

--

Percent chord Percent chord

(C) a1 4.0°, 92.9° (d) a1 6.0°; 8-4.3!

0 20 40 80 80 100 o 20 40 60 80 100 Fttent chord Percent chord

(e) a,9.7°; 9=6.30 (f) a,I5.00; 88.2!

Figure 47._ Blade-surface pressure distributions and blade section characteristics for the cascade combination, = 600 , a = 0.50, and blade section, NACA 65-410.

24 .8

20 .7

o 9 __

- ----_ C

— 0 Gd1-----

. owl

16 1.— .6

80 - .08

70 - .07

60 - .06

50 - .05

C D

d1 40 - .04

12 1— . 5

deg cit

8— .4

4 , - .3 /

-4 .1 -

-8 - A

30 - .03

20 .02

10 - .0!

0-0

NACARM L51G31

115

4 8 12 16 - -

.

a /, deg

(g) Section characteristics ; arrow shows design angle of attack, flagged symbol indicates leading-edge roughness

• . 4. Figure 47._ Concluded.

0 • 011 0 20 40 60 80 IC

----I

116

NACA RM L51G31

:442.4

- 1.6

1.6 S

S

8 .8

C')

"0 20 40 60 80 100 "0 20 40 60 80 100 Percent chord Percent chord

(a) a, 1.40 ; 8 4.6. 0 Convex surface a Concave surface (b) a,=5.30 ; 8- 73?

1.6

1.6

S .8

S .8

Percent chord Percent chord (C) a,=73°; 9=8.3° (d) a,&0; 8 =9.5

3.2

a4

S 1.6

.8

0

.52

24

S 1.6

.8

C")

O 20 40 80 80 100 Frtent chord

(e) a,13.20 ; 9=12.0°

Figure 48. - Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)'

0 20 40 60 80 tOO Percent chord

(f) a,171 0 ; 8=12.4°

distributions and blade section combination, l = 600 , 0.50,

LO.

80 -1 .07 24 - 12

20 - II

16 - 1.0

70 -H .06

II 0 8

13 CII

Cd,- -

A. cwI

-

tz

—7

/

/____

60 —I .05

50 —I .04

I d 40 H .03 -

.9

8, deg— Cli

30 —1 .02

20 .0I

10 ''] 0 0 4 8 12 16 20

a,, deg

(g) -Section characterTsiTs; arrow ihois design angle of attack,

flagged symbol indicates leading-edge roughness.

Figure 48.- Concluded.

0—.6

-

NACA EM L51G31 117

118 ItIACA RM L1G31

1.6 S

- .8

S

Lb

.8

1.6 S

5ô406080,00 00040080100 Percent chord Percent chord

(a) a,4.20 ; 9=82° (b) a1 8O°, 9=11.7?

o Convex surface o Concave surface

1.6

S .8

0) 20 40 60 80 00

Percent chord (C) a1 = 9.7 0 ; 6=12.50

on i I I I I 0 20 . 40 60 80 100

Percent chord (d) a1 = II.7 0 ; 9=14.00

a4

S 1.6

.8

0 r

3.2--I I

-

24-------

S I.6-----

------

- -p

0 20 40 60 80 100 Frcent chord

(e) a1 13.7 0 ; 0=14.9°

Figure 49. - Blade-surface pressure characteristics for the cascade

and blade section, NACA 65.-(18).

"0 20 40 60 80 100 Percent chord

NOW (f) a116.50; 6=15.4?

distributions and blade section éonibination, 0= 60, a 0.50,

LO.

16 1.0

o) deg H cI

40 —1 .04 cw

Cd

30 —i .03

NACA RM L51G31

119

for-DD

24 1.2 .06

20 Ii

50 —1 .05

''I

20 .02

10 .01

0 0 4 8 12 16 20

,, deg

(g) Section characteristics ; arrow shows -design angle of attack;

flagged symbol indicates leading-edge roughness.

Figure 49.- Concluded.

8 .8

.4 .7

0 .6

24

1.6 S

.8

.42.4

1.6 S

.8

C.'

120 NACA EM L51G31

0 20 40 60 80 tOO

20 40 60 80 100 Percent chord

Percent chord

(a) a,0.2?; 90.3°

(b) a1 3.30 ; 94.1°

r Cnnuv !.Irfnr o Concave surface

1.6

1.6

S .8

S .8

) 20 40 60 80 100

20 40 60 80 100 Percent chord

Percent chord

(c) a1 6.I 0 ; 84.8

(d) a1 9.30 ; 87.4?

a4

S 1.6

.8

0

24

.S 1.6

.8

0 20 40 OD 80 tOO o 20 40 60 80 100 Frcent chord Percent chord

(e) a,9.80 ; 8t2.4° (f) a118.101

Figure 50.- Blade-surface pressure distributions and blade section characteristics for the cascade combiriion, i = 60°, a = 0.75, and blade section, NACA 65_1410.

0 .2

-4 .1

-8L_ 0

k.1

1.2 .5

8 .4

deg Cl'

NACA RM L51G31

121

70-1 .07

60 .06

56 .05

40 —1 .04 C

& Cdi

30 .03

20 .02

10 .01

0 0 0 4 8 12 16 20 a,, deg.

(g) Section characteristics ; arrow shows design angle of attack,; flagged symbol indicates leading-edge roughness.

Figure 50.- Concluded.

-

122 NACA BN L51G31 loop

2.4

1.6

S

.24

1.6

S.

S 1.6

.8

0

S 1.6

.8

.8

020406080100 Percent

(0) a,3.20 ;chord 8- 780. o Convex

o concavesurface (b)

Percent a, =6.20 ;

chord 9=10.8' surface

1.6

S .8

0 I I I I I 0 20 40 60 80.100

Percent chord (C) a, = 9.2 0; 0 =

a4

1.6

S .8

0 I I I I I I 0 20 40 60 80 tOO

Percent chord (d) 9=4•5

3.2

24.

.0 20 40 80 80 tOO 0 20 40 60 80 toO Frcent chord Percent chord

(e) a, = 13.2°;, 0 -16.21 (f) a, =18.20; 9=19.5°.

Figure 51.- Blade-surface pressure distributions and blade section characteristics for the cascade combin4Lon, 600, 0.75, and blade section, NACA 65-(12)lo..

NACA RM L51G31

123

70 .06

60 .05

50 .04 C

L&

Cd, 40 .03

30 .02

20 .01

10 0 0 4 8 12 16 20

(g) Section charãbteristics arrow shows design angle of attack; - flagged symbol indicates leading-edge roughness.

Figure 51.—Concluded.

1.0

20 .9

16 .8

8, deg— C11

12 .7

8 .6

4 .5

0 4

O 20 40 60 80 K30 0 20 40 60 80 100 Percent chord Percent chord

(C) a,-15.10 ', 8-20.7! (d) ,1700,82.7.

3.2

a4

S 1.6

.8

0

- 0

24

S 1.6

.8

0 204080 100 Percent chord

(e) a,19.0° 8=22.7

Figure 52.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(18)

80 100 )rd 8=22.7°

section a = 0.75,

Percent chi (f) a,22.0°;

distributions and blade combination, 01 = 600, LO.

121# NACA RM L51G31

24

I 6. S

.8

2A

LE S

.8

0 1 !I :.s I

Percent chord.

(a) 1=9.20; 9=I5.8

0 Convex surface D Concave surface

20 40 60 80 100 rcent chord

(b) , I2.06 , 8=18.30

Lb

S .8

S

ii

16 - .7

12 - .6

A—c

30 - .02

20— .01

In - 0

NACA RM L51 G31I -

125

32 i— II .06

0 8

a C11 C -L -o--

i C::I _1

Tfl

28 1.0

deg H c1

20L—.8

60 —1 .05

50 -H .04

D81

40 —I .03

8 - 12 16 20 24 - -

a, deg (g) Section characteristics ; arrow shows design angle of attack.

Figure 52.- Concluded.

2.

1.6

S

.8

126

NACA RN L51G31

24

1.6

S

.8

MEME IEW'40= V

MMM MENEM

terceni chord Percent chord

(a) a,= 0.00 -, 9 = 2.8 (b) a,: ao°, 8=_ 0.9° o Convex surface ° Concave surface

Lb

S .8

----5

1.6-

01 - MMMI Percent chord Percent chord

(C) a,: 400; 8:080 (d) a,=6.0°; 6:270°

- --

S 1.6

24

S 1.6

.8

- 0

- - -

-o o 40 W 80 100 0 20 40 60 80 100

Percent chord Percent chord (e) a,=I0.0 0; 0=5.9° r() a,16.00; 8=11.1°.

Figure 53.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, i = 60, = 1.00, and blade section, NACA 65-010.

NACA RM L51G31

127

08

0 6

C11

o. Cd 1 . - H 40

Cw I -

—30

_1 . 1111 120

24 r.5

20 —4

16 .3

.12 —.2

.07

.06

.05

8 —.1

deg— C1,

4-0

.04 C

& Cd1 .03

—1 .02

4 H-.2 9

-8 L I I V 10 0 8 12 16 20

a/, deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 53.- Concluded.

128

NACA EM L1G31

24

1.6

1.6

S

S

.8 .8

IMENEVIES

Percent chord Percent chord (a) a1=1.00. 6:2.10 (b) a1=4.00-

o Convex surface a Concave surface

1.6

S .8

0- -- -- JO

Percent chord Percent chord

(C) a,: 6.0°; 0 = 6.4°. (d) a,=8.00; 8=7.90.

3.2

2.4

1.6

.8

00 20 40 03 80 100 '0 20 40 60 80 100

Frtent chord Percent chord (e) a, : I0.00; 8 : 100°. (f) a,: 15.00; 9:126°

Figure 54.- Blade-surface pressure distributions and blade section characteristics for the cascade'conibiiation, = 600, 1.00, and blade section, NACA 65-410.

1.6

S .8

0

24

S 1.6

.8

C.,

70 1 .07

60—j .06

5O— .05

o '.e o C1

G Cd1

A Cw1

0

28

24 •—.7

20 —6

16

deä_Cz1

40-1 .04

CW

L H a

Cdj 30 .03

NACA RM L51G31

kill129

I

vz^

I 0 0 - 1 0 4 8 12 16

a/, deg

(g) Section characteristics ; arrow shows design angle of attack.

Figure 54. Concluded.

8 [--..3

4 I— .2

0 '— .1

S 1.6

.8

0

S 1.6

.8

0

130 NACA RM L51G31

1.6 S -

.8

1.6 S

.8

b 20 40 60 80 100 '0 20 40 60 80 100 Percent chord Percent chord

(a) a,=6.70, 8=10.2°. (b) a,8.7°; 8=11.5!

o Convex surface ° Concave surface

1.6

S .8

1.6

S .8

09 H I I I 0 20 40 60 80 tOO

Percent chord (c) a,=I0.7° 8=I3.3

0' I I I I I 0 20 40 60 80 100

Percent chord (d) a,=12.70 , 8=14.6°

a4

24

O 20 40 60 80 100 . 0 20 40 60 80 100. Percent chord Percent chord

(e) a, : 14.7 0; 616.1 0. (f) a,: 16.7°, 8=16.5°.

Figure 55.- Blade-surface pressure distributions and blade section characteristics for the cascade combi'hation, 0 1 = 60, and blade section, NACA 6-81o.

NACA RM L51G31 1k 131

iL' 1I

Li

7P

zzll'o

•

----2^1-

--

4-3 110 1 0 4 8 12 16 20

a,, deg

(g) Section characteristics ; arrow shows design angle of attack -

Figure 55.- Concluded.

24 r—.a

20 -.7

16—.6

O,deg--Cz

- 12 --.5

8 I— .4

60 .05

50-H .04'

40— .03. cw

L_ '

30— .02

ac —I .0

24

1.6

S

[:I S

132 NACA RN L51G31

:8 fiTft.L U U '10 bU U IUU U 20 40, 60 80 100

Percent chord Percent chord (a) a1 = 4.20 ; 8= 9.0°. (b) a 8.20 ; 9 13.50.

o Convex surface ci Concave surface

1.6

S .8

0

LE

S .8

0 D 0 20

Percent chord Percent chord (C) a = 12.0 0 ; 9 16.90 . (d) a= 14.20; 819.0°.

3.2 -

2.4

S 1.6

.8

0

24

S 1.6

.8

n0 20 40 83 80 100

Percent chord (e)a,=17.7'°; 9=21.60

Figure 56.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)

0 20 40 60 80 100 Percent chord ItIryAL (f) a. =21.7 0 ; 8 = 22.5°.

distributions and blade section coination, 13j = 600 , 1.001

LO. -

NACA RN L51G31

133

24 .- .8

O,deg—, Cli

20 L- .

32 1.0

28 .9

12 H- .5

16 F— .6

0 9 -

C11

-C1

A Cw1

FT

-.

.1

70--1.06

60—.o5

50 - .04 Cw

LEk

Cd 40 - .03

30 -1 .02

_

8 L_- 10 -J 0 4 8 12 16 20 24 deg -

(g) Section characteristics arrow shows design angle of attack;

flagged symbol indicates leading - edge roughness; solid symbol indicates high Reynolds number.

'Figure 56.- Concluded.

134

NACA RM L51G31

ZA

1.6

1,6 S

S

.8 .8

r I

Percent chord I Percent chord

(a) a,=8.0 0 914•9 0 (b) a,=12.0°; 9=19.50.

o Convex surface a Concave surface

1.6

S .8

S

21-

0' I .1 I I

0 20 40 60 80 100 Percent chord

(C) a,=14.00 0=21.5°.

2.4

U 0 20 40. 60 80 100

Percent chord (d) a, : 15.5°, 8=22.7°..

32

24

S 1.6

.8

00 20 40 60 80 100

Percent chord Percent chord (e) a1 =16.5 0; 9=23.00. (f) a,=19.50 8:23.7°.

Figure 57.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 0 1 =600

1 Cr = 1.00, and blade section, NACA 65-(15)10.

S 1.6

.8

0(

06

- D Cl 1 -

G Cd1

- C

Ax

- L—

<-

L I

.24H.8

20 - '.7

O,deg C11

16 - .6

2 I— . 5

8L4

NACA RM L51G31 - 135

28 i-- .9 60-1.05

50— .04

40 - .03 CwI

d1 30 - .02

20 -H .01

10 _j 0 8 12 16 120

a/, ' deg (g) Section Characteristics ; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness.

Figure 57.- Concluded. -

4

S 1.6

.8

0

S 1.6

.8

0

136

NACA RM L51G31

1.6

1.6

S

S

.8

A "0 20 40 60 80 tOO

Percent chord (a) a,=lQO°, 0:17.4°.

0 Convex surface I I I

o Concave surface

8

A "0 20 40 60 80 100

Percent chord (b) a 1 = 14.0°, 9=21.9°

1.6

S .8 .8 I-

01 I r I I I 0 20 40 60 80 tOO

• Percent chord (c) a,: 16.0°; 0=24:2°.

3.2

Z4

Rei 0 20 40 60 80 100

Percent chord (ci) ci,=17.5°, 0=25.2°.

24

0 20 40 6D 80 tOO Percent chord

(e) a,=20.0°; 0=26.40.

Figure 58.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(18)

0 20 40 60 80 100 Percent chord

(f) a, = 22.00, 0=26.3°.

distributions and blade section combination, l -

a = 1.00,

24 .8

0, deg — C11

20 I— .7

40 —1 .04 I C.

L —1I

b7

CdI 30 -H .03

NACA RM L1G31

137

32 60 06

28 F— .9

50 -H .05

16 I— .6

2 I— . 5

0 e

o C11

G Cd1

CwI

a H .02

LIi—t?1

0 —J 0 12 16 20 24.

deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 58.- Concluded.

-, . .

8 L

138

NACA RM L51G31

I

24 24

1.6

1.6

S

S

020406080100 Percent chord Percent chord

(a) a,=12.0°; 618.5 1. (b) a,=16.00; 9=24.9°.

o Convex surface ° Concave surface

.8

0(

1.6

S .8

1.6

S .8

0

Percent chord - (C) a, : 18.00; 8=26.6°.

3.2--I I

--

24

S

0 20 40 60 80 100 0 20 40 60 80 100 Percent chord Percent chord

(e) a,=21.5°, 9=27.8° c a,=23.5 0 , 9=279°.

Figure 59.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, Jl 6o°, a = 1.00, and blade section, NACA 65-(2.1)10.

0' I I I 1 I

0 20 40 60 80 100 Percent chord

(d) a,19.50 ; 8=27.10.

S 1.6

.8

0

N&CA RM L51G31 139

a 3D LV

32 .9

28 .8

24 .7

0, deg— Cl1

20 .6

16 .5

12 .4

8 E.3

(V .01

60 .06

50 .05

40 .04 cw.

Dd1

30 .03

20 .02

10 .01

0 n- 8 12 16 20 24

a,, deg

) Section characteristics ; arrow shows design angle ' of attack; flagged symbol, indicates leading-edge roughness.

Figure 59.-*ic1uded. .

24

sI.

111.0

24

1.6 S.

.8

NACA RM L51G31

S 1.6

.8

0

5 1.6

.8

0

0 20 40 60 80 100 "0 20 40 60 80 Percent chord - Percent chord

(a) a1 0.00; 8 =-0.4! (b) a, = 6.00 , 0=5.6!

o Convex surface o Concave surface

1.6

S .8

1.6

S .8

0' I I I I I 0 20 40 60 80 K0

Percent chord (C) a, = 80°; 8=7.50

a4

0 20 40 60 80 tOO Percent chord

(d) a,=I0.00, 0=9.20

3.2 1 I

24

0 20 40 60 80 tOO 0 20 40 60 80 100 Percent chord Percent chord

(e) ä, =14.0 6; 0=13.0? Y(f) a,=20.00; 8=1530.

Figure 60.- Blade-surface pressure distribjtions and blade section characteristics for the cascade combinion, O l =

600 , - = 1.25, and blade section, NACA 65-4iW.

111.1

50 .06

40 .05

30CW

d1 20 .03

10 .02

NACA RN L51G31

.3

0, deg__- C11

8 .2

4 .1

20 .5

16 .4

0 6

E3 C21

0 Gd1

A •Cw1

0

0 .01

-4 -I 1 0

a1 , deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

'Figure 60.- Concluded.

1.6--

S .8__ -

- _ -

01

S .8 I—

142 - ----V NACA RM L51G31

24—____

C

O- I I I - 0 20 40 60 80 100 0 20 40 60 80 100

Percent chord Percent chord (a) a1 = 8.1°; 9=I3i (b) a,=12i°, 9=17.40

U I I S

.I •_

o W 40 60 80 100 0 20 40 60 80 100 Percent chord Percent chord

(C) a, = 14.1 0 ;.9=19.6 o (d) a1 = 16.I°; 9=21.4°.

32

S 1.6

.8

0

.i2

24

S 1.6

.8

0 '20 40 80 80 100 Percent chord

(e) a,=20.I 0; 9=24.3° 40 Figure 61.- Blade-surface pressure

characteristics for the cascade and blade section, NACA 65-(12)

0 20 40 60 80 100 Percent chord

(f) a,=2410; 9=25.2°

distributions and blade section combination i 60°, a 1.25, LO.

60 .06

50 .05

40 - .04. cw

81 D

d1 30.O3

PO .02

10 1.01

-

NACA RN L51G31

111.3

32 F__ . .9

8 L - - 0 '0 8 12 16 20 24 28

a1 , deg

(g) Section characteristics ; arrow shows design angle of attacks

flagged symbol indicates leading-edge roughness.

Figure 61.- Concluded.

28 i- 8

24 - .7

deg-

20—.6

16 F— ..5

1

12 ^— .4

0 6

E3 C11

i

D (

( >T-

2.4

NACA EM L51G31 144

24-

1.6—

S

.8.

o

1.6

S

.8

0 20 40 60 80 100 00 20 40 60 80 100 Percent chord Percent chord

(a) a,=12.00; 8=172°. (b) a,=16.00; 8=24.40

o Convex surface • - a Concave surfarp

1.6

S .8

1.6

• S .8

01 I 1 I I I 0 20 40 60 80 K0

Percent chord (C) a,=18.00;

OZ

2.4

01 I I I I

0 20 40 60 80 tOO Percent chord

(d) a, = 20.0°; 0=28.8°.

NACA

I I I_

24 I

S 1.6

.8

0

1.6

n

--

-

1-0-1 1 r

0 20 40 80 100 Percent chord

(e) a, : 22.0°; 8=29.9°.

Figure 62.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(18):

0 20 40 60 80100 Percent chord

(f) a, = 24.0 0 , 8=30.0°.

distributions and blade section combination, '3 i = 60°, = 1.25, LO.

NACA RN L51G31

36 H .9

32 H .8

28 i- .7

deg —CZ,

24 I- .6

0.9

o C11

CdI

CWI

L D

\\.1K/___

70—I .06

60—I .05

50— .04 C

0

40— .03

20 i- ,5

30—I .02

6 - .4

12 I— 12 16 20 24

10—j n

a deg

(g) Section characteristics ; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness.

Figure 62.- Concluded.

[:1

1.6

S

I 1.-i

146

NACA EM L51G31

4

6

S

#% fl# aa 1a aa

U V V MU DV DV I(.A) U () 'IU bU t5U IOU

Percent chord Frcent chord (a) a,=O.O°; 8=-3.9 (b) a, = 4.00; 8=0.00.

o Convex surface Concave surface

O 20 40 60 80 00 0 20 40 60 80 100 Percent chord Percent chord

(c) a, = 6.0°; 8 : 23°. (d) a,=8.0*-,8=410

2

S I

--1 I

020408D80100 020406080100 Percent chord Percent chord

(e) a, : 12.0 0; 8-7.7 (f) a,16.00; 8=11.00.

Figure 63.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01'= 600, a 1.50, and blade section, NACA 65-010.

NACA RN L51G31 147 -

o 9 - 20 1.— .4 D; C11

30—.07

G Cd1

A .Cw1

16 - .3

20— .06

10— .05

8—i

0) deg - Cz1

4-0

0--i

-4 -

-24 8 12 16

20 40 0

a/ , deg

(g)

Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 63.- Concluded.

Asnow

o - .04 C

L

C-I UI

tO— .03

-20— .02

30— .01

RRIN

NACA RN L51G31

•q.

1.6

1.6

S

S

.8

0 20 40 60 80 . 100 00 20 40 60 80 100 Percent chord . Frcent chord

(a) a,:3.00; 9:350 (b) a, : 6.O°; 9=6.3°

0 Convex surface ° Concave surface

8

1.6

S .8

a4

S 1.6

.8

0

1.6

S .8

) 20 40 60 80 Percent chord

(d) a1=11.00;

3.21

241f I

S 1.6

.8

.0

Percent chord (C) a,=9.6*, 9:990

Fol 0

020406380100 0 20 40 60 80 100 Percent chord Percent chord

(e) a, : 1300, 9:1290 _]L (f) a:1900, 9:1440

Figure 64.- Blade-surface pressure distributions and blade section cbractèr1stics for the cascade combin&ion, 600, a 1.501 and blade section, NACA 65-410.

NACA EM L51G31

2 .5 50 —i .05 o 9

a C11 C1 i CWL/

X0

—f' 4LI"—L

40 —H .04

30 .03

L D

Cd, 20 .02

16 I— .4

12 - .3

8, deg— Cl,

.2

4 F— .1

fl L_ o 0 -J 0 - 0 4 8 12 16 20

a,, deg

(g) Section characteristics ; arrow shows design angle of attack.

Figure 64. - Concluded.

4

6

2

S

1.6

S

150 NACA RM L51G31

.8

n, aa #.a a U KV 94U OV OV RiO LI O. '40bO dU IOU Percent chord Percent chord

(a) a, = 3.7 *; 8 : 6.4°. (b) a,: 9.7°, O=132!

o Convex surface o Concave surface

1.6

S .8

00 20 40 60 80 100 0 20 40 60 80100

Percent chord Percent chord (c) a1 :12.70; 8 : 16.0? Cd) a,=I4.7 0 8=177°.

3.2

S 1.6

.8

0 • 0 20 40 60 80 100 0 20 40 60 80 tOO

Percent chord Percent chord (e) a, : 17.70; 8 : 20.5° . (f) a, : 23.7 0; 9:200e

Figure 65.- Blade-surface pressure distributions and blade section characteristics for the cascade' combinion, = 600, = 1.50, and blade section, NACA 6-81o.

1.6

S .8

n

32

24

S 1.6

.8

()

NACA RM L51G31 151

15 A - -70 .06

60 .05

50 .04 C

L D

Cd 40 .03

30

20 .01

10 0 4 8 12 16 20 24

0

a, deg.

(g) Section characteristics; arrow shows design angle of attack.

Figure 65. - Concluded.

.1

20 .6

16

8, deg C11

12 .4

8 •

4 .2

0

I....

IMIN•

ME oil

Ori

Lb

S .8

S

)O

0

distribution coinbinatiqn,

LO. -

20 40 60 80 100 Percent chord

a,=28.I°; 8=27.6°

s and blade section 600 , a = 1.50,

152 NACA RN L51G31

)O

OMEN ••iu• • IMMMEM i r.A m 16 c.. 192. M.. M 'm •

• • iI... I I I .1 :s •s

2

1.6 S. S

.8

Percent chord Percent chord (a) a,=8.I°; 9=13.1°. (b) a,12.I0 , 91790

o Convex surface a Concave surface

Percent chord Percent chord (c) a,=I6.I°; 8=22.4.° (d) a,=18.I 0 ; 8=24.2°

3.2---

0 20 40 80 80 100 Percent chord -

(e) a1=22.I°; 9=27.3°

Figure 66.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)

2.4

S 1.6

.8

0

36 .8

321— .7

28 .6

8, degCl

24 .5

20 1-- .4

9L 0 C21

G Cd1 f

- A 0w1 _

b L

-

. --- - -

- - -- -

- -

- - -

-I

EiI I; 3 16 20 Th Th

70 -i .06

60 —H .05

50 —1 .04 I

LCw

EN 0

Cd1

40 .03

30 —I .02

NACA RN L51G31-

153

20 .01

10 0

a1 , deg (g) Section characteristics; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness.

Figure 66.- Concluded.

S 1:6

.8

0

S LE

.8

(1

1514.-

NACA RM L51G31

24

1.6 EQ

1.6

S

.8

ow I' I I I I

0 20i 40 60 80 100

I 0 20 4060 80 100

Percent chord Percent chord (0) a,=12.0 0; 8=18.9° (b) a1 160°; 8=24.5°

o Convex surface o Concave surface

1.6

S .8

1.6

S .8

0''èl

Percent chord (C) a, 18:00; 8 = 27.2°.

0' I 1 1 I 0 20 40 60 80 100

Percent chord (d) a,= 20.00 , 8=28.81

32

2.4

24

0204080I00 Percent chordchord Percent chord

(e) a, : 24.00 ; 8 =32.0°. (fl a,28.00; 0= 30.9!

Figure 67.- Blade-surface pressure distributions and blade section characteristics for the cascade combinatfln, i = 600,a = 1.50, and blade section, NACA 65-(15)10.

28 i- •5

deg C11

24— .4

40 —I .03

I L

Cw

CdI D

30 .02

NACARML51G31 .155

36 1 .7

32 F— .6

C

G Cd1

.Gwl

D

60 .05

50 .04

i i t

20 .01

10 0 12 16 20 24 28

deg

, g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 67.- Concluded.

20 •

16

M NONE RIV

MEiiui

.6

S .8

S

.2.4

S 1.6

24

S 1.6

-

156 •NACA RM L51G31

1.6

1.6

S

S

.8 .8

C)0 20 40 60 80 100

Percent chord Percent chord (a) a, : 16.00 ; 8=24.7° (b) a,20.0°; 9:30.1°.

0 Convex surface El Coneava qurfnea

0 20 40 60 80 100 0 20-40 60 80 tOO Percent chord Percent chord

(C) a, : 22.00; 9=31.90 (d) a,=24.0 0; 9:33.60.

.8

0

.8

00 20 40 6D 80100 0

Percent chord _ (e) a,=28.00; 934 .9°. .L (f)

Figure 68.- Blade-surface pressure distributions characteristics for the cascade combin4ion, and blade section, N&CA 65-(18)lo.

20 40 60 80 tOO Percent chord

a,: 32.00; 0=36.00.

and blade section Ol = 600, a 1.50,

NACA RM L51G31

157

4 I .9

36 F— .7

32 j- .6

0, deg— dl 28 i- .5

o •9

c C21'

G Cd1

A owl

L i —L,_^

70 -i°

60 -H .06

50 —1 05

40 -H .04 ICw

L D &

CdI

30 .03

24 .4

20- •

16 - .2

20 —1 .02

11.— Iii

0 _Jo 12 16 20 24 28 32

a/, deg

( g ) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 68.- Concluded.

158 NACA RM L51G31

• 1.6

1.6 S

S

.8 .8

)0 Percent chord Percent chord

(a) Q,: 19.0°; 8=29.8 0. (b) a,= 22.00; 8=32.20

o Convex surface n Concave surface

0 20 40 60 80 100

1.6

S .8

1.6

S .8

0

Percent chord (C) a,:25.00; 8=36.0°.

o 20 40 60 80 100 Percent chord

(d) a,=27.00 ; 8=38.0°.

0

OX

2.4

S 1.6

• 77

0 20 40 60 80 tOO Frcent chord

(e) a,=30.0°; 8=38.1°

Figure 69.- Blade-surface pressure distributions and blade section characteristics for the cascade combinatilon, Ol = 600, a = 1.50, and blade section, NACA 65-(21)10.

.8

0

NACA RM L51G31 -

100 .IU

90 .09

80 .08

70 .07

60 .06

C a

CdI

50 .05

40 .04

30 .03

20 .02

10 .01

0 6 20 24 28 • 32

a/. deg -

Section characteristics; arrow shdws • design angle of attack.

- -. -Figure 69.- Concluded.

56 I.'

52 1.0

48 .9

44 .8

40 .7

0, deg Cz1

• 36 .6

32 .5

28 .4

24 .3

20. .2

.1

159

NACA RN L51G31 160

2.

1.6

S

.1J)Li'i

2

LE

S

wIn..uv surface

LE

S .8

O"S 05 .09:1814 Iercent chord

(C) a,;2700; 9=40.0°.

01

I -

Q I I I IJ 0 20 40 60 80 100

Percent chord (d) a,= 27.0°; 8=39.20

•:L+ 0 20 40 60 80 100 0 20 40 60 80 100

Percent chord Percent chord (0) a,= 23.o°; 9 = 34.9 0 (b) a,= 25.00; 9=38.10.

- 0 Convex surface rt - -

LE

s .e

S I.E

.8 - - - - -

DC

0 20 40 60 80 100 Frcent chord

(e) a,=29.00 ; 8= 39.20

Figure 70.- Blade-surface pressure di stributions and blade section characteristics forthe cascade combination, i = 600, a = 1.50, and blade section, NACA 65-(2i. ) 10. .

/

60 .06

50 .05

40 —I .04 I Cw

LI1 D1&

1 Cd 30 —1 .03

a —1 .02

NACA RN L51G31 .. 161

32

0, deg— Ci,

28 .4

24 F— .3

40 r— .7

36 H- £

vr^^

a C21

G Cd1

- Cw1_ I Ii20 I— .2

16 L_ .1 0 —so 20 24 28 32

a1 , deg

(f) Section characteristics', arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 70.- Concluded.

• __

C

162 N.ACA RM L51G31

2.4

1.6

1.6

S

S

0 0 20406080 00 Percent chord Percent chord

(a) a,=0.06; 8=-2.4° (b)a,=2.O°; 9=-0.4°.

o Convex surface a Concave surface

.8

0

1.6

S .8

1.6

5- .8

0 20 40 60 80 100 Percent chord

(c) a1 =4.0°; 9=I.51

0' I I I I I 0 20 40 60 80 100

Percent chord (d) a,=6.0 0 ; 8=3.10

r

S I

3.2

2,4

S LE

.8

('I

0 20 40 80 80 tOO -- Percent chord chord Percent chord

(e) a,=9.00; 95.00 - morwil") a,=15.00; 9=7.7?

Figure 71.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 700, 1.00, and blade section, NACA 65-010.

16H- .3

deg C11

8 H..1

4 0

0.

-4 H-

NACA RM L51G31

24— .5

20— .4

I l 0 9

0 C11 -o---G Cd1 10 -H .06

-: ;'- /2.___

o —J.os

0 —1.04 IC

W

F 5p, 0 -H.03.'

Icd1

0 —.1.02

/

T"

s—r1

163

10 i .07

0 -J 0 0 4 8 12 16

a/ , deg .

(9) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness, solid symbol indicates high Reyndids number.

Figure 71.- Concluded.

164 NACA EM L51G31

2A

1.6 LE

S S

.8 .8

0 20 40 60 80 100 0 20 40 60 80 Percent chord Percent chord

(a) a, =0.5 0; 8=0.7° (b) a,=45°; 8=4.50

o Convex surface E3 Concave surface

• 1.6 16

S .8 S .8

0

-- JO

Percent chord Percent chord

(c) a,=6.5 0, 8=5•90• (d) a,=8.5 0; 8=7.70

3.2 --

2.4

S 1.6

.8

0K) 020406080100

Percent chord • Percent chord (e) a1 =12.5°; 8= 10.00 1 rIIt f a, = 16.5 0 ; 8=10.30

Figure 72.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, = 700 , a = 1.00, and blade section, NACA 65-410.

24

S 1.6

.8

0

165

--1.08

NACA BM L51G31

24 r .6

ó 8

- a C11

G Cd1

A Cw1

--

'20

20 1— .5 0 .07

50----1-.06 16 I— .4

10— .05 C

a CdI

$0— .04

0, deg

to-H .03 4 I— .1

10-H .02 rem ^I

-4 F—.1

0_J ó a1 , deg

(g) Section characteristics ; arrow shows design angle of attack, flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynods number.

Figure 72.- Concluded.

4

I I

S

10 0 20 40 60 80 tOO

1.6 1 1 L 1

166 -

NACA RN L51G31

4

1.6

6

S

S

.8

I"

- 0 11570M.'s L, 10

Percbnt chord Frcent chord -

(a) a, : I.20; 8:340 (b) a,5.20; 8:6.9° o Convex surface o Concave surface

Percent chord . Percent chord (c) a1 = 7.2°; 8:86 0 (d) a,=9.2°, 9:104°

24

- S 1.6

S .8

()'0 20 40 6D 80 100

Ircent chord (e) a, : II.2°; . 9:1180 CO

Figure 73.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-810.

0 Percent chord

a,=15.20; 9:I20.

distributions and blade section combination, 01= 700 , a-= 1.00,

to .02

0 .01

-1.0 0

- o: 4 8 12- 16 a,, deg

(g) Section characteristics *,arrow shows design angle of attack; flagged symbol indicates leadin9-edge roughness; solid symbol indicates high Reynolds number.

Figure. 73.- Concluded. .

167

7O—.08

60 .07

50 .06

40 .05 cw

Cd1 30 .04

20 —1 .03

NACA RM L51G31 *

Co .7

24 I.— .6

20 :5

16 .4

8, deg C11

• 12 .3

8 .2

4 .1

0 0

-4 . - i

24

1.6 S

2

S

168

NACA EM L51G31

:EFttPt 0 20 40 60 80 100

Percent chord (a) a,3.I°; 8=6.2°.

o Convex surface o Cnnenv sirfnr

1:6

S .8

S

B 1!r-

20 40 60 80 100 Percent chord

(b) a,=8.60; 8=11.8°

l

:M

PIP, fin

0 20 40 60 80 tOO 0 20 40 60 80 tOO Percent chord Percent chord

(C) a,=I0.6 0 ; 8=13.3° (d) a1 =12.60 ; 9=14.4°.

a4

S 1.6

.8

0

24

S 1.6

.8

020 40 60 80 tOO

Percent chord a1 =16.60 ; 8=15.21

and blade section

131 = 700, a = 1.00,

0 20406J80 tOO Percent chord

(e) a,=14.60 ; 0=14.8! (f:

Figure 74._ Blade-surface pressure distributions characteristics for the cascade combination, and blade section, NACA 65-(12)10.

•1 o8•.••• j1 D C21

- C1

WI

^N

D

—4

T/L

• .06

0 .05

0— .04 C

& )•

CdI

0— .03

.02

NACA RN L51G31

169

• 24 .9

20 - .8

16 - .7

dew— C11

• 12 - .6

4—.4

.n -•

0 .01

0 4 8 12 16 20

a/, deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness.

Figure 74.- Concluded.

COrg_-

1.6

S .8

.0

Percent chord (d) a1 =12.0°, 9=1621

170 NACA RM L51G31

2

1.6 S

S

.8 .8

o 20 40 60 80 100 '0 20 40 60 80 100 Percent chord . Percent chord

(a, a1 =6.0°; 8=9.8°. (b) a, =8.0°; 0=13.0,0

o Convex surf ace Concciv i,rfnt'c

Lb

S .8

Percent chord (c) aç10.0°; 8=145°

3.2-

H

S

.8 -------

0 20 40 GD 80 I 0 Frcent chord

(e) a,=14.0°; 9=14.7°.

Figure 75.- Blade-surface pressure distributions and blade section characteristics for the cascade coination, 01 70 = 1.00, and blade section, NACA 65-(15)10.

171

-

50-1.05

40 - .04 Cw

D81

Cdj

L

3Q - .03/

NACA EM L51G31

20 1— .7

16 h .6

Ode Cl1

2 I- .

loss

06

oC11- G Cd1

Cwl F^'

A I/Al

24 -.8

8 I— .4 20 —.I .02

4 I— .3

S

4 8 12 16 0 - 0

a, deg

(f) Section characteristics no design point was obtained; flagged symbol indicates leading-edge roughness, solid symbol indicates high Reynolds number.

Figure 75.- Concluded.

4

S 1.6

.8

0

S 1.6

.8

0

172 NACA RN L51G31

24

ZA

1.6

1.6

S

S

.8 .8

Percent chord Percent chord (a) a,2.0°; 817° (b) a,6.0 0; 8=5.2

o Convex surface n r.,in-ntn . - w. V I U.0

Lb

1.6 -

S ' .8

S .8

01 I I I I I 0 20 40 60 80 100

Percent chord (C) a,=8.0°; 8=6.7°.

0•' I I 1 1 I

0 20 40 60 80 100 Percent chord

(d) a1 =I0.0°; 9=8.61

aX

3.2

a4

24

0 20 40 6D 80 tOO Percent chord

(e) a,=14.00 ; 8=11.30.

Figure 76.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65_41o.

0 20 4060 80 100 Percent chord Nftrm (f) a,1a0°; 8=11.7!

distributions and blade section combination, 01 = 70°, a = 1.25,

NACA RM 1,51G31

173

20 .5

16k— .4

12 .3

- O i deg C11

8L—.2

I I 0 e

D C11

—G Cd1

A Cw1

-

50 i .05

40 .04

30 .03 Cw

& Cd1

20 .02

I— .l

0 —J 0 .0 4 8 12 16. 20

a1 , deg

(g) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 76.- Concluded.

L_ 0

174

NACA RM L51G31

H

4

1.6 6 S

S

.8

B

.

C o 20 40 60 80 100

Percent chord Percent chord (a) a, 4.7°; 8=6.1°. (b) a = 8.70 ; 9= 10.4?

0 Convex surface n Concave surface

LE

S .8

0

Percent chord 0

T Percent chord c) a, = I0.70; 9i2.0? (d) a,=12.7°; 8=13.8?

32

S 1.6

.8

00 20 40 &) 80 tOO "0 20 40 60 80 100

Percent chord -. Percent chord (e) a =14.7°; 8=1461 . a,=16.70; 8=14.6?

Figure 77.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 70 , a= 1.25, and blade section, NACA 65-810. -

11 I I I ) 20 40 60 80 Ic

I! 0 S. ..:rm

24

S 1.6

.8

NACA RN L51G31

175

70 .06

60 .05

50 .04 C

DCdI 40 .03

30 OF-

20— .01

10 0 0 4 8 12 16 20

a1 , deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Flgure 77.- Concluded.

24 •

20 .7

16 .6

0, deg zi

12 .5

8 .4

4 .3

9

176 NACA RM L51G31

S 1.6

.8

0

S 1.6

.8

(1

1.6

1.6 S

S

.8

P.0. 20 40 60 80 100 . '0 20 40 60 80 100 Percent chord Frcent chord

(a) a,=6.I°; 8=7. 1 0 (b) a,=IO.I°, 9=I3.41

0 Convex surface a Concave surface

1.6

S .8 .

- 1.6

S .8

0

O0 FT- - - -

-_- -

0------- 0 20 40 .60 80 tOO 0 20 40 60 80 100 Percent chord Percent chord

(c) a,=I2J 8:15.6 0. (d) a,=14.I°; 9=17.00:

3.2

2.4

24

20 40 60 80 100 Percent chord

a, : I8.I 0 ; 0=17.00.

s and blade section = 700, cr = 1.25,

0 20408O tOO 0 rcerit chord

(e) a,=16.I 0; 9=17.00. U _____

Figure 78.- Blade-surface ,pressure distribution characteristics for the cascade combination,, and blade section, NACA 65-(12)10.

2 I— .4

0 4 8 12 16 20

deg

(g) Section characteristics, arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 78, Cdided.

NACA RN L51G31

32 r .9

28 1— . 8

24 I- .7

20 - .6 .6

9 ) deg— Cu

16 1- .

--t 177

—i07

so -H .06

50 —1 .05

40 —1.04 ICw

CdI 30 —i .03

8 I— .3

L_ .2

178

24_____

C ..1

2.1

SI.(

NACA RN L51G31

.8

o 20 40 60 80 100 . "ó 20 40 60 80 100 Percent chord Percent chord

(a) a,IO.O°; 8 : 13.5? (b) a,I2.0 0 ; 8I6.I°.

o Convex surface ° Concave surfnt'ø'

)0 Iercent chord Percent chord

(C) a1 14.0 0 ; 8185°. (d) a,=16.0 0 ; 8=19.70

3.2

2.4

S 1.6

.8

0

1.6

S .8

0.

• 1.6

S .8

0 0

w 0 20. 40 &) 80 tOO

'Percent chord (e) a,=18.0°; 8=19.70

Figure 79.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 700, a = 1.2, and blade section, NACA 65-( 15) 10.

NACA RM L51G31

179

2 .8

24 I— .7

20 H .6

deg— 9z

16 L- . 2 H .

60 .05

50 H .04

40 —i .03 I Cw L

Cd, 30 —1 .02

20 —1.01

8.39 I I16 '

I I I . 0

• 8 ' 12 20s'

a,, deg

(f) Section characteristics; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 79.- Concluded.

• __

)0 Percent chord

(d) a,=8.O6; 82.8°

S P1

I!

24

S • 1.6

.8

(J

180 r

NACA RN L51G31

1.6 S

S

.8 .8

0 20 40 60 80 100 0 20 40 60 80 100 Percent chord Frcent chord

(a) a,0.O°; 8-3.6°. (b) a,4.00; 8:_I.o° o Convex surface 13 Concave surface

FEW".". MEN Ij!

MENEM ME SoMew '14

Percent chord (C) a,=6.0 0 ; 8=0.8

S I

0 20 40 6) 80 100 o 20 40 60 80 100 Frcent chord Percent chord

(e) a,12.0 0 ; 86.5°. (f) a,160°; 883°.

Figure 80.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = = 1.50, and blade section, NACA 65-010. 4

NCA RM L51G31

2 ,

20 1— .3

16 1— .2

12 .1

deg— Cli

4 F— .I

01— .2

-4 l-- -

ilL 181

0 —1 .07

0 —1•05

0 —.02

[I-Mn

0 —1O Icw

Cdj 0 —j.03

- - -- _[i.— T

deg

(g)

Section characteristics ; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 80.- Concluded.

182 NACA EM L51G31

24

1.6

.8

1.6

S

.8

0. '20 40 60 W IW0(

10 Percent chord Percent chord

(a) a, =0.00 , 8=_o.30 (b ai r-4.0% 9=2.9?.

o Convex surface o Concave surface

S I-II - 0 20 40 60 .80 100 0 20 40 60 80 100

Percent chord . Percent chord (C) a,: 8.0°; 9=6.8° (d) a,=I0.0°; 8=8.2°

3.2

2.4

S 1.6

.8

00 20 40 OD 80 100

Percent chord (e) a,: 14.0 0 ; 9=1 1.6°.

Figure 81.- Blade-surface pressure characteristics for 'the , cascade and blade section', NACA 65-41o.

1.6

S .8

24

S 1.6

.8

()0

distributions combintion,

20 '4060 80 100 Percent chord

a,I8.0°, 8:11.8°

and blade section 01 = 700 , = 1.50,

0 e - - 5

.n C11 .

—ó Cd1.

_

___ ___

I I

006 2 I— .5

16 I— .4

0 —1 .04. IC

Ek Cd1

0 -H .03

12 .3

8, deg

0 -H .02 4 f— .1

10 10 0 4 8 12 16 20

a,, deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 81.- Concluded.

- .-.. .

NACA RM L51G31

183

1.6

S .8

0 0

1.6

S .8

0

184

NAQA RN L1G31

1.6 S

2 .

1.6 S

.8 .8

-----I

Percent chord Frcenf chord (a) ,g4 •70; 85.I. (b) a,8.7 0; 810.20

o Convex surface a Concave surface

)0 Percent chord Percent chord

(C) a,:I0.7°; 812 . 1 0. (d) a1 12.70 , 8=14.00

3.2

2.4

S 1.6

.8

00 20 40 6D 80 100

Percent chord Percent chord (e) a,14.7 0, 8=15.7? _________________ (f) a1 18.7 0 ; 8=1740

Figure 82.- Blade-surface pressure distributions and blade section characteristics for the cascade combination, 01 = 700, = 1.50, and blade section, NACA 65-810.

24

S 1.6

.8

C)

a

NACA RM L51G31

I I

o 9

Cl1

Cd1 5 A Cw1 -

L - J. / \

4

A^l 3

V) A^y

•

2

1 w .

24ç .7

20 F— .6

16-5

6, deg- C11

12 - •4

8H.3

4 h .2

185

0 —i .06

0—I .04 CwI

Ic

0— .03

0 —1 .02

mom

O--- I - __ I0_J0

8 12 16 20

a,,deg

(g) Section characteristics ; arrow shows design angle of attack; flagged symbol' indicates leading-edge roughness; solid symbol indicates high Reynolds number.

• Figure 82.- Concluded.

Z4

HS 1:6

.8

.0

32

24

S 1.6

.8

ri

- 186

NPCA RN L51G31

0 20 40 60 80 100

.4 - - - -

.6 - -

20 40 60 80 100 Percent chord Frcent chord

(a) ap8.l°; 9:900 (b) a, : 12.1 0 ; 8=15.90.

o Convex surface a Concave surface I. I! !1

o 20 40 60 80 tOO 0 20 40 60 80 100 Percent chord Percent chord

(c) a1=14.1 0; 9 : 182° (d) a1 =16.1 0 ; 9:1970

S

I 1° 1

0 20 40 60 80 tOO Frcent chord

(e) a,: 18.l°; 9:20.6°.

Figure 83.- Blade-surface pressure characteristics for the cascade and blade section, NACA 65-(12)

0 20 40 60 80 tOO Percent chord

(f) a,: 20.1 0 ; 8:1970

distributions and blade section combination, 1l = 700, a'= 1..50,

LO.

NACA RN L51G31

24 - .7 I I 09

- 0• C1

20— .6-0Ca1 CwI

- - L D

16 - .5

9deg — Czi

12 .4

187

60 .06

50 —1 .05

40 —I .04 Icw

L D

CdI 30 .03

8 F— .3

20.02

0—J0 12 16 20 24

a1 , deg (g) Section characteristics ; arrow shows design angle of attack;

flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

Figure 83.- Concluded..

4 - .2

flL I

H188

NACA RM L51G31

2

I.E

S

1.6

-S.

.8

o

.8

- 0.

Per chord, Percent chord (a) a1=I20°; 9=13.2°. (b) a,= 14.00; 8=1700.

C Convex surface o Concave -aMMM OU

1.6

5' .8

'0

1.6

S .8

0 0 20 40 60 80 100

Percent chord Percent chord (C) a1 = 16.0°; 920.4 0. (d) a1 18.0°; 822.2°

3.2

P-4

S 1.6

.8

0

24

' S 1.6

.8

(1020 40a) 80 100.. C)

Percept chord (e) a,= 20.00 ; 8=22.50. (f)

Figure 84.- Blade-surface pressure distribution characteristics for the cascade combintion, and blade section, NACA 65-(15)lo.

20 40 60 80 100 Percent chord

a,=22.00; 8 23.50.

s and blade section = 700, a = 1.50,

tso I

189 NACA RM L51G31

44

40 1.0

36 .9

32 1.8

O ideg —

Cli

28 .7

70 .07

60 .06

50 .05 C

L

CdI 40 .04

30 .03

fla C11

—G Cd1

A Cw1

24 .6

20 .5

$6 .4

12 .3

20 .02

10 .01

n12 $6 20 24

a1 , deg

(g) Section •• characteristics ; arrow shows design angle of attack; flagged symbol indicates leading-edge roughness; solid symbol indicates high Reynolds number.

,Figure84. - Concluded.

Cd1

Cd1

199 NACA RM L51G31

28

24

9) deg

20

1€

12

o 450 1.5 - fJ 450 15 turbulence added -

60° 10 turbulence added

- -- - -

E

140 180 220 260 300 R

340 380 420 460 500 x103

(a) Variation with R near design angle of attack.

Figure 85.- Effect of Reynolds number on turning angle and drag coeffi-cient of the NACA 65-(12)10 blade section for typical cascade combinations.

NACAE14 L51G31

101

40--I I I I I I 1.1 I

0R :245000 smooth blade 0 R :445,000 smooth blade turbulence added

36 OR :245,000 leading-edge roughness added - ZO= - - .07

_06

---- -

28-------------- --05

8, deg ----------------------1----. Cdi

24---'

20--

.02

12III ;E::IIIIII Cd1

01

1 .. 8 LL8 12 16 20 2428 .3236 0

a,, deg

(b) Comparison for the angle ,-of -attack range for 8:450, o-1.5.

Figure 85.- Continued.

.4

-

.07

.06

.05

.04

Cd1

.03

.02

192

NACA RM L51G31

32I I I

- o : 245,000 - - - ' 0 R = 445,000

28

24

20

8, deg

6

2

Cdl,/

8 .01

4

0 0 4 8 12 16 20 24

a/, deg

(C) Comparison for the angle-of-attack range for

8 :60°, j- =1.0 smooth blade:

Figure 85.- Concluded.

NACA RM L51G31

16

193

12

8

CP

0

C

I, C 0

a) C/)

-8

300

--- -

- = - -

70° -

450

70° - 60° --- - - - - - -

- - -

-300

-120 4 8 12 16 20 24 28

Comber, C20

Figure 86.- Variation of estimated operating angle-of-attack range- with camber for the inlet angles tested.

194 0.00 NACA RM L51G31

1.0

.9

.8

.7

.6

.5

.4.

.3

.2

0.

REMEMMEMEM SMEMEMEMEM MEMEMMEMEMMMUNMEMEME MEMERMUME MONEEMEMEM MEMMEMEMEM MEMEEMEMEM

I. __I___

MENOMMEMEM EMOMMEMEMEMEMESOMMEMI

MEMOMMOMME MMMMMMMMMM MIMMEMOMMEM MENNENno MENEM___ -s:,

0 1 F I MENEM NONE

1. g.

Turning angle 9 Figure 87.- Variation of ideal and test dynamic-pressure ratio across

the cascade.

1

i.II_\iIIII?

0

-

eiC

'-4

4.)

o

•

(D r()

U •a)

cJ r()

o

- j4)

ODr-4

c'J o

- C

bD 04

c •,-C -j E 0

D

cliCd cc

L) (D • .

(0 •0Ct) rlW O)Q)

ii.

NACA RN L1G31

195

ci - - - -

E

196 NACA RM L51G31

2.0

16 'C a

E 0

b12

a w a) E

.8 0 0.

0 o .4 0 -j

[I,

/

Ideal -

Test

.4 .8 12 16

Solidity, o-

Figure 89.- . Variation of the limit loading parameter, (Ocz)max with solidity for inlet angles of 600 and 700.

NACA RN L1G31 197

2E

24

20

I6

12

8, deg

8 0

4

0

-4

-8

/

-

/ 1

/-

I

- 7/H-----

---.-- 7 --

IIII'2IIIII Present data -

Data ref.4 - -

- -- 0 65-010 -

0 65-410 Q 65-810 --

--- - - - -'

- E 65-(18)10 - -

• ___

• 0 4 8 12 16 20 24 a, deg

Figure 90. - Comparison of turning-angle, : angle-of-attack relationships for the present porous-wall cascade results with those for the solid-wall cascade of reference 4 for a typical combination, 01= 600, a=l.00.

----- .198 O_ -W

'NACA EM L51G31

44. -

40- - - -'--

36-

/

28 -.

• .. /

24

8, deg -

• H./•

-

/ 7 /- .065-010

065-4I0

-. ./ 065-810 ____74_- • A65(I2)10

• / :. 65- (15fl0 - •65-(I8)I0

-• —/-7--. --------

0 -4 -. - - - - - - --

-. --. - I I 0 ' 4 8 12 16 20 24 28 32 • 36

a/ , deg

Figure 91.-Sunnnary of turning'angle, e,- angle of attack, a, relation- ship for the blade sections tested at • = 300 , a = 1.00. Short

• bars across curves indicate design points.

NACA RM L1G31 199 -,

-4 0 4 8 12 16deg

20

24 28 32 36 40

Figure 92.- Sim ary of turning angle, e, angle of attack..-.a. relation-ship for the blade sections tested at 01= 30°,cr = l.25 short bars across curves indicate design points.

200

NACA RN L1G31

2

9) deg

2

48 ------------_________

-- ----

- -- -- -

-_7_-

----/ - /77

----- -- :0--- -

If-- -7 - - ---- --

-/ ---065-810

65-02)10

- 65-(18)I0

7 7 - 965-0I0.

- -7------- 65-(15)1Q_ -

_ 7Z /-I----

0 -- 7/ - - - - - - - -

-

--_I I-. a lb 20 24 28 32 36

a1 , deg

Figure 93.- Suxmnary of turning angle, e, angle of attack, a, relation-ship for the blade sections tested at 01 = 30, a = 1.50. Short bars across curves indicate design points.

- __

NACA RN L51G31 -- ir 201

-

2

2

6deg

4

0- -

6

2

o'65-410_ 4i 65-'(12)I0

65-(18)I0-

00

/ _____ I•L 4 8 12 16 20 24

a1 deg

Figure 9L- Summary of turning angle, e, angle of attack; a, relation-ship for the blade sections tested.at -li.5°, = 0.50. Short bars across curves indicate design points.

202 NACA RM L51G31

32-

28 - -

-

24 —

0, leg

16 ----/

- - - - - -

7

I2

- -- -, -

8 -- -- --

-

--- 0 65-410 - 7A 6512)10

/

00 4 8 12 16 20 24 28 a,, deg

Figure 95.- Summary of turning angle, 0, angle of attack, a, relation-ship for the blade sections tested at 01 a = 0.75. Short bars across curves indicate design points.

NACA RM L51G31

203

48 -

44 - - -

40 -

36 - - -

32 - -

28-----

24 -

O,deg

20 -

16

12

8

065-010 65-410

4 065810

0 A 65(12)I0 65-(I5)I0----65-(I8)I0

0 065-(21)l0----

7 0 65-(24)10

-d

---------- 065-27)l0----

• 0 48 12 16 20 24 28 32 36 a,, deg

Figure 96.- Summary of turning angle, e, angle of attack, a, relation-ship for the blade sections tested at 01 450, a = 1.00. Short. bars across curves indicate design points.

4C

3€

32

28

24

O,deg

20

6

12

8

4

0.

2O1. NACA RN L51G31

v lb 7.0 24 28 32 36 a,, deg

Figure 97.- Summary of turning angle, e, angle of attack, a, relation-ship for the blade sections tested at Ol = .5°, a = 1.25 . Short bars across curves indicate design points.

NACA RM L51G31 . . . 20

--,-

--/ --

48

_

40 1)'

KY -

32--------------------

20

28______77 ---

O,deg --------- _

24 ----------2--_-______ -

0'

_

- _

/ 065-010 0.65-410

-065-810 7 7 t 65-fl)

• -__Z t65-(I5I0 • 7 . C65-()I0

4 . 065(2010

/ . 065-(24)l0

• __ 0_7

-.

0 4 8 12 116 20 24 28 32 36 40

- - a, deg

Figure 98.- Summary of turning angle, e, angle of attack, a, relation-ship for the blade sections tested at 0 1 450 , a = 1.50. Short bars across curves indicate design points.

8

206

NACA EM L51G31

• _/; •_____

—t •

•

__ • 065-410

)( •L 65-(12)I0

___ ___ ___ ___ • -

b 65(18)I0—_

00 4 8 ' 12 16 20

a/ , deg

Figure 99.. Suary of turning angle, e, angle of attack, a, relation-ship for--the.-blade sections- tested at • = 600, = 0.50. Short bars across curves indicate design points.

V /

V

NACA RM L51G3].

241 I

20

16

0, deg

2

8

I

•//

V . .. .

65-410 :65-(I2I0

65-(18)I0-

4. 8 12. .16 20 24

deg

Figure 100.- Summary of turning angle, e, angle :of attack; a, relation- ship for the.b1ade sections tested at = 600, a = 0 . 75 . Short bars across curves indicate design points.

208 NACA EM L51G31

3

2

24

2C

16

O,deg

12

8

4

0

-4

a, deg

Figure 101.- Summary of turning angle, 9,angle 3f a ttack, a, relation- ship for the blade sections tested at I3 60'y cm = 1.00. Short bars across curves indicate design points.

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

IIIIII7?IIII --

--- - jr, - -7,-----

- ---7 0 65IQ D65410 c65-8Io

65-(12)I0 b 65 -C15)10

65-(18)I0 Q 65-C2DIO

7

- , .- . -

72

- -

i.

4 8 12 16 20 24

- A1, -

NACA RM L51G31 209

0 4 8 12 16 20 24 28

deg

Figure 102.- Summary of turning angle, e, angle of attack, a, relation-• ship for the blade sections tested at i = 600, a = 1.25. Short bars across curves indicate design points.

100W. S

NACA EM L51G31

-4 - 0 4 8 12 16 20 24 28 32 36 -

Figure 103 . - Summary of turning angle., 0, angle of attack, a, relation- ship for the blade sections tested at = 600, a 1.50. Short bars across curves indicate design . points.

a,, deg

-------_--_•-____

210

4

4C

36

32

26

24

deg

20

16

2

8

4

0

• -

----

-

-

-

••

-• -

---•--

-

--

--

7-- - -- 065-0I0 -

0 65-410

065-(24)I0

L /' <>65-810 7 /) • A 65 -(12)10 / 65-(15)I0 7 / C 65-(18)10 • / 0 65-(21)I0

-

NACA RM L51G31

16

12

8

O,deg

4

NSA _

VP'1165-410

-

im

-4 0 4 8 12 16 20 deg

Figure 104.- Suniniary of turning angle, e, angle of attack, a, relation-ship for the blade sections tested at 01 = 70°, = 1.00.' Short bars across curves indicate design points.. -

I]

-4

212 :'th NACA RM L51G31

16

IN

deg

8

4

_ •

___ ___ ___•

________

• 065-410 - 65-8I0 •

t 65-(12)I0 65-(I5)10

___ ///J ______

___

___ ___ ___

0 4 8 12 16 20 deg

Figure 105.- Summary of turning angle, 0, angle of attack, a, relation-ship for the blade sections tested at 01 =700,. a = 1.25 . Short bars across curves indicate design points.

• : ______

NACA RM L51G31

4 V

"'e I --il— I /t

",/T

• ___________

• 9 K /• 065-010

/ 065-410 65-8IO

___ A65—(12)10

___ 2 ' •

• 0 4 8 • •. 12 16 20 24 •

• a'deg • •

Figure 106.- Summary of turning angle, •e 'angle of attack, a, relation-ship for the blade sections tested at 01 = 70°, a = 1.50, Short

bars across curves Indicate design points. I

214 NACA RN L51G31

10

O. .4 .8 1.2 1.6

Solidity, •-

Figure 107.- Variation of turning-angle, angle-of-attack slope at design withsoiidty and inlet angle.. The slopes are averages for the moderate camber range.

Solidity, o•

Figure 108.- Variation of design angle of attack with solidity for the sections tested.

- •65-(27)I0

-: 65(24)I0

•- 65-(2l)l0-

F 74

- 65-(18)10 •

-65-(l5)l0_ •

-

/(/ V65-410 -- -

/-

--

-

V_

- -

.4 .6 • .8 tO 1.2 • 1.4 1.6

32

28

24

U 0 4-

•1-o 16

0

0

112 0 0

8

4

C

NACA RM L51G31 215

NACA RM L51G31

-300

-65-(24)I0 -

IIIIIIIII:i10 • •t/ / - 6515)I0

- 65-(12)10

-

7Z

----------i /-/--

/ r:_ - 65-810

7/7 / ------

Lj

---

65-010

__ _

216

4

4

4c

3€

3

co

- 2€ 0

C 0

c 24 C 4-

C

2C 0

1€

- 2

8

4

0 .2 4 .6 .8 1.0 1.2 1.4 1.6 Solidity, a-

(a) Inlet angles of 30 0 and 450

Figure 109 . - Variation of design turning angle with solidity and inlet angle for the sections tested.

XAQA RM L51G31

217

65-(21)l0 IIIIIIIiIII-i 60°

--70°

$ .-------- 7 -

--

-

---/7--- --

- 65-(- 5)10

/

-

-- -

-- - - 65-(I2)lO

-

----------

--

-

----

—65-81 - C

-

7 7

_2Z—65-4 l(

'--_--

-- 65-010 __

36

32

28

CD

C 0

C C U.

20 C

a,

16

2

B

4

i:. .2 .4 .6 .8 1.0 1.2

1.4 1.6 Solidity, o

(b) Inlet angles of 600 and 70°

Figure 109.. Concluded.

1

NACA EM L51G31 218

40

36

32

01.0 o 1.25

1.5

28

a

C 624

0I C C 1..

4-

20 C

'A 'A

16

65-(18)10-1

-(12)101

F1

8

65-410

4 1 I 1 I I 1 1 I I I 30 40 50 60 70 80

Entering air angle,

Figure 110.- Variation of design turning angle with inlet angle and solidity for typical sections.

on

Bep•Po puo P D sejbuo ub!è!èQ

±

\._ i,

\ r \ \\ \\ ----\\\\ __ _0

0

%1) ,—•1

0)

0)

0 a)

I')

C.)

0 a

.,-1 C)

in

a

O4

0

cc Cc

H H

NACA EM L51G31 219

0 to o

I1 i iIII

co 0

-±--+_J IIIIII"" iIIIII±.II

OD

CD

N

In'

2 I.

'-I

(1)1)

'- to p

220

NACA EM L51G31

w 0 o0 c.J oJ c.J

bep ' P8 p1 'seibuo u5199Q

• ___

NACA RM L51G31 low**

221

------------------QL

---

-- - --! ---,-

---

- ---- -- - —f--- 0 W CD oO

bep' 9 puoz, 'saibuo u!Saü

--

InH

0

-

__\_ --

--

----------

----H— -V-C^v r----

---s

-

-

it; on _

) hi

'I

o on

0

0 I-a)

. t E 00

on

a)

jc-)

r-1 i

222NACA RM L51G31

bep '9 puD D 'SaIbUD u6isaj

NACA RM L51G31 . 223

a)

C 0

ts

U) a)

C 0

C 0) U) a)

--

44

--

40

36--/ - --' --- - - -

.VI 3a // --- -- -

/7 28 - 77- ---7/--

z 7. 20 7

/ ---. --

- /----- - ___

_---

4 _

, or. I I I 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4

Camber, C1 0

(e) Solidity of 1.50

Figure lii.- Concluded.

NACA-Langley - 9-14-51 - 325'