PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM … · 2011. 5. 14. · REPORT NADC-79081-60 S\WI OF PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM EFFECTS FOR TWilL NAVY GAS

$Page 1: PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM … · 2011. 5. 14. · REPORT NADC-79081-60 S\WI OF PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM EFFECTS FOR TWilL NAVY GAS$
REPORT NADC-79081-60

S\WI OF

PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM EFFECTSFOR TWilL NAVY GAS TURBINE ENGINE CODE, NEPCOMP

W. H,. BallThe Boeing Company

Seattle, Washington 98124

I11 October 1979 r

Final Report for Period 28 June 1979 through I11 October 1979

Contract No. N62269-79-C-0278

Approved for Public Release;Distribution Unlimited

Prepared forNAVAL AIR DEVELOPMENT CENTER

Warminster, Pennsylvania 18974

~-~17

UNCLASSIFIED

SZ9L*fASFCTO O. TTTIS PAGE (Whe DolEntred

S. ERO RMNG ORANAT DON PME TAND IDES PAGE RO EA D EIMNST.ROUCT.ITAS K

II.CONROLIN OFIC NAE ND DDESSEFORE OMPETN FR

ARcrf &ME Cre System Technology Diecort 11P' CAe~TALO7NUBE

7amntr PA8 187(A UnUas fiBd

P /AIJ -oAPI IVLUAIONOF ROPISIN 2 DueCLSFIATO DOcawNGRADIN7SCHEDULE

16. DITRIBUION ECSTEMT (Of GAS: TURBINE

* Unlimite

IS. PERPLEMINT RARY NATO N AEADADESES RGA LMET Rj .TS

Nohze Poerformpance ,1 ,-. 'r

Nahlcir us velfor mn Cete3.NMBRC.PAEWamistr PA, 1897

DD I AN 711473EDITIN OFI NOV65 I OBSOETlanclasifie

SECURIT IS. CLASSI IFICATION ODOWNGPAE RA4~.lDaeEING a)

SCHEDUL

NADC-79081-60

FOREWORD

This report describes the work performed at The Boeing Company on

Contract N62269-79-C-0278. The work was performed during the period

28 June through 3 October 1979.

During the contract the existing PIPS[ and DERIVP computer codes

previously developed for the U.S. Air Force were modified to operate on

the NADC computer system and a training session was held at NADC to

explain the operation of the codes and to demonstrate its usage to NADC

personnel.

Mr. John Cyrus was Project Monitor for NADC and Mr. W. H. Ball was

Program Manager for The Boeing Company. Modifications to the computer

code were accomplished by Mr. R. A. Atkins, Jr.

SJN

S..... • " • 4

NADC-79081-60

CONTENTS

List of Illustrations i

List of Tables vc.. - • vii

List of Nomenclature and Symbols, ' ix

Introduction _.

i i .

Modifications to PIPST Code -

* Preparation of ADEN Nozzle Mdps 7

Calculation of Installed Perfor~nance 7

Demonstration and Training Session 7

• Appendix A: Installed Performance Calculations 9

Appendix R: General Computer Program Operating Characteristics 29

References 47

S~iii

St

NADC-79081-60

LIST OF ILLUSTRATIONS

SFIGURE PAGE

I NAOC Uninstalled Engine Data Input Format 2

2 Format for TAPE7 (Installed Performance) File 5

A-1 Maximum Engine Airflow for Turbofan Engine 12

A-2 Maximum Engine Airflow for Turbojet Engine 12

A-3 Comparison of Installed Performance for Various Inlet 13Configurations at Mach 2.0 (Turbofan Engine)

A-4 Comparison of Installed Performance for Various Inlet 14Configurations at Mach .80 (Turbofan Engine)

A-5 Comparison of Matched Inlet Total Pressure Recovery 15for Various Inlets (Turbofan Engine)

A-6 Comparison of Matched Inlet Drag for Various Inlets 15(Turbofan Engine)

A-7 Comparison of Maximum Installed Thrust for Various Inlets 16(Turbofan Engine)

A-3 Comparison of Intermediate Installed Thrust for Various 16

Inlets (Turbofan Engine)

A-9 Inlet Drag for a Normal Shock Inlet with a Turbofan Engine 17

A-10 Inlet Drag for a Mach 2.0 Inlet with a Turbofan Engine 17

A-il Inlet Drag vs. Pow2r Setting for a Mach 2 Inlet 18With a Turbofan Engine

A-12 Comparison of Installed Performance for Various Inlet 19Configurations at Mach ?.0 (Turbojet Engine)

A-13 Comparison of Install-id 2e'-formance for Various Inlet 20Configurations at Mach .80 (Turbojet Engine)

"A-14 Comparison of Matched Inlet Total Pressure Recovery 21for Various Inlets (Turbojet Engine)

A-15 Comparison of Matched Inlet Drag for Various Inlets 21(Turbojet Engine)

A-16 Comparison of Maximum Installed Thrust for VariuuS Inlets(Turbojet Engine)

M3 LUNG PAM B"K - NOr 111.04

NADC-79081-60

LIST OF ILLUSTRATIONS (CONTINUED)

FIGURE PAGEA-17 Comparison of Intermediate Installed Thrust for Various 22

Inlets (Turbojet Engine)

A-18 Inlet Drag for a Normal Shock Inlet with a Turbojet Engine 23

A-19 Inlet Drag for a Mach 2.0 Inlet with a Turbojet Engine 23

A-20 Inlet Drag vs. Power Setting for a Mach 2 Inlet 24With a Turbojet Engine

A-21 Catalog of Permanent Files on NADC Computer Account 25A-22 Nozzle and Aftbody Area Distribution for a Twin ADEN Nozzle 26

Configuration

A-23 Drag for a Twin ADEN Nozzle Configuration 27

A-24 Gross Thrust Coefficient for an ADEN Nozzle Configuration 28

B-i Description of PIPSI Program and References 30

B-2 PIPSI Analysis Process and Files Utilized 31

B-3 PIPSI Interactive Input Options 32

B-4 PIPSI Data Flow 33

B-5 Matrix of Inlet Maps in Library File 34

B-6 Matrix of Nozzle Maps in Library File 35

B-7 ADEN Nozzle Configuration Available as a Separate Input File 36

B-8 Illustration of the Derivative Process 37

B-9 Example of a PIPSI Terminal Session 38

B-10 Example of a DERIVP Terminal Session 41

Vi

I.

NADC-79081-60

LIST OF TABLES

a TABLE PAGE

A-I Summary of Installed Performance Calculations 10

A-II Summary of Inlet Capture Areas 11

I:.

• 4• ~vii,,•

NADC-79081-60

LIST OF NOMENCLATURE AND SYMBOLS

* Ac Inlet capture area, in2

Ao Local stream tube area ahead of the inlet, in 2

AoI Free-stream tube area of air entering the inlet, in 2

CD Drag coefficient, , dimensionless

C-D Convergent-divergentDADD diesols

CDADD Additive drdg coefficient, CD ADD dimensionlessGOD DADD_ q AC

* CDA1 0 Afterbody drag coefficient, DRAG , dimensionlessq A10

CDBase Base drag coefficient, (bP Abse , dimensionlessCqoio"

CDAIOA9qA1 DCDPAP Drag coefficient, q0 (A10 -A9) , based on

projected area, dimensionless

CfG, Cv Thrust coefficient, F dimensionless

D Drag, lb.; hydraulic Diameter, 4A , in., diameter, in.P

FN Net thrust, lb.

FNA Installed net thrust, lb.

M Mach number, dimensionless

PT Total pressure, lb/in2

SPT2 /PTo Total pressure recovery

SFC Specific fuel consumption

SFCA Installed specific fuel consumption

T/F Turbofan

T/J Turbojet

W Mass flow, lb/secWC, WV'/r Corrected airflow, lb/sec.

OT;2 Temperature correction factor, TT2 /lSTD.

N 2-D nozzle wedge half-angle

p Round plug nozzle half-angle

Six............1(

NADC-79081-60

INTRODUCTION

The purpose of the contract work was to modify an existing Air Force/

Boeing computer code (PIPSI, documented in References 1 through 4),

install the modified code on the NADC CDC computer sjotem, and train NADC

personnel in the usage of the code by means of instruction and

demonscr ation.

The complete documentation of the calculation methods employed by the

code, nomenclature, sample cases, and the library of inlet and

nozzle/aftbody input maps is contained in the set of documents

(References I through 4) which describe the code developed for the Air

Force version of the program. This report describes those changes to the

existing code that were made to adapt the code to the NADC computer and

to provide the desired output data.

MODIFICATIONS TO PIPSI CODE

The modifications to the computer code that were accomplished t0 make the

code compatible with the NADC computer system and the NADC inpu: data

format are described below.

Changes in Uninstalled Engine Data Format

(1) The format of the uninstalled engine data for the NADC version of

the PIPSI program is slightly different from that described in

Section 6.6 of Reference 2. The engine input data format for the

NADC PIPSI code is shown in Figure 1. The only difference from the

original code is that the areas input for AS and A9, shown in

NADC-79081-60

WALS .30(liv,1.0l 10Sl IP11.' : Pile, ý-; l • ( --], ?: A/F- Ptf.' -' P&)P'A,"PCF W-FCi,,

• 000 0. 1 . 0 0 .1 35 .35.--4 . f 31 1,.o 0 ?. pP.,i 4 W ], 17.9 .• O

--] .UO 0 ). 2.00 ?3453.27114.4, 316.u ?.PA 0 440.4 417.9 .'yo5t)

.ioo0 0. 1.00 23S45,36;-04.6 316.0 ?.013 493.4 417.9 .90 09 .2000 0. 2.00 ??096.27733.3 316.0 2.945 43FA.1 417.9 .vbO 0

' .. . 0 Oo 0. -- -.-. 4J2 -I--, nl , (-, 1-2- -. • P___, I 16, -4)- -- c- )7x-4-- 3ýF,-I-A,-,----4-j-7-,, 9 -- bO 0 .... I

.40U0 0. 1.00 ?4?37.3875-3.3 "1]A.1 3.177 485.7 417.9 .0 t0.4000 1. ?.no ???7Q.29 '-It.9 316.1 3.?] 1 431.4 417.9 .1700o. -000..-.. . - 3.Dn ?01cc.I0 -214 f1 3 3. - -376.-3-4-27.--1ýo J;).6000U (. 1.00 c2672.4?'--4.f, 31?.? 3.q73 477.? 417.9 . 1o00o6000 O. ?.00 r233Q7.32':-ý1.7 31?.2 3.610 424.0 417.9 . 'c'0 1

- -,.bO00 --..... .----3. Q -~(0 •0 75 3 1-. ... •1 -? -3 ;4 - -.4- -1- 7..9--.... I10

1. 1.00 ?63(U0.45%]t..u 2L,4.4 3. F 0 476.6 4)7.9 . o0')t4 .00 0 0. 2.00 ?3P 4 4. 3 531. 1 ?94.4 3.40?.) 4?J. F Y11.9 . 7od0

'........ 0.0 . . .. 3 - -- 3 .4- .4 17. ---..- %v J0S .U00(0 0. 1.00 27644.50101.1 ?73.7 4.?7?. 475.9 '.17. C .C 01 0.000 0. 2.00 24747.3813b.5 R273.7 4.317 4 22 ., 417.9 .Sb0 0

,. ...1-- O0(0 ---.....- ") '------3 .4-' -- ?---7-i-. ?-7-~4 .- 6----?-73 .- 7.... X ..qr--L7 ... 3 . C4- --4 1-7-. 9-- 4.-o0 J] .,000 0. 1..00 ?9 0o.51 75.3 ;?4].o 7,.71. 47P.Q 417.9 47 .t-. 47

-1.,(00 0.. .o .. P00 .S707,-1 1., ?.-1 . 70-,t--, 4??•. e.17. -9 0-sO)

~ (10U In000(s. 1.00 17oo 2-.t1.2 3?4.b 3.0]'4 . 417.9 .9o0i.2000 111000 . 2.00 163P0.20141.4 724.t 3. 0'4 452.0 417.9 .t00

_'e --.- 1() )o o- O,0 --- -1.00 1 1 .4U?4. 1- .., -1 .3--"?i - I . ..-o -- - .4. n - -393 .. 7- -. 1 7-. 9- ..... 4 ,..I4 1 .100( 0 t 10 U. 1.00 17773.2W574.1 3-?.7 3.?rs7 •0 3 .2 417.9 QJ*. r),

.4000 1000(1. ?.00 16331.21L?4.0 ?F?.? 3 .P 446.5 1v l. v .t0o)S .000- 10Oi .. 3.f -]47,.1 -. ? --... ?1-.-7-1 .?.3P--)--3A9.0 - 179. -.-.- '.)t ,

, .0U0 0 10060. 1.00 11-572.310F5.3 31F.0 3.60-1 496.5 417.9 .9t%00.6000 10000. 2.00 ]6q?7.23ý?Oo.ý- 316.0 3.64-4 440.8 0 ,7.9 .Po0,.)

t) ) 0.. . r0n --1 0 0 . -- (141]0 -- 15] 7 4 . 17 -ý _-.-2 ,---] . -- 3 .- •- -3 A 4 4 -- 17 --- •--

:1 .t00o 100(,0. 1.00 ?n3I1.36((1-9 6 f-. 1 . 4 -j 4 j'0.] 417.'• .',o0.)n• 000 10UV 0 ). P_. 00 1](300 . ?7- 1 o.L 3]F-.. 4 .401) 4,2h.6- ]7. Y • 11)

... ..... 00-10U041.--- 3.60-.1-7112.. 1J--7].7 31..e-- ..441-- 37?.0 -41]7."-).- v. oUI.UO00 0oO0. 1.00 2'09Y.39'9e3.4 2?47.b 4. 'Ob 476.7 417.9 .Y t,.1.0000 10000. 2.00 ?0604.3U 13.t- ?P 7.o t . 01;3 423.6 4,7.9 'o,),)

1 .200 110)000 . 1-1.00 ?43I? .4 31-1 '1 27 .3 -H 434 4n 7- 417.9 9c:ijI L0 )1 U 0 0 0 0 (. 2.00 2 1 Q n. 339•.- L-5 P7 3. .Ln 47P7.9 4] 7.9 . o,;) 1)1 .0( 10 , q . 0 1]bf¢•,.? 0, 7 L-'7 •-A cý-- .c 3 W 0•. - 4 17. 9- . 0) :.4000 ?0(016. 1.00 1Ž537.?0,hF.7 327.1 3.?'in '25.3 417.9 .9oj1

4 •U 20L000. _.00 ]1517.15 -7., 327.1 3.34b 465.6 417.9 .'o:)94.1)4 11 ?rnm00 .- 0 ...3.0 n ]-10 7.-111-•)0.7-- 3-7-.1- 3. 7- -- 05.?-47.. ---.$LOM.c-000 20000. 1.00 13 4P4.2ŽL)5.5.r 32_.0 3.7.5 b 14.? 4 17.9 *900)

b .60 0) .00(10. 2.00 1??R-.173,0.3 3 ?.O 3.7un 456.0 417.9 .7ou00.00 ?oo20G0n. -3.00 -110o].2119.1-% . 25.u 3.-R31-37.1 4137.9-- 147-h 0U0 2,0000. 1.00 1501,7.2557H.4 3 19.5 4.3P0 c01..8 417.9 .;c00.•0000 20000. 2.00 ]3600.19 -17.1 319.t 4.43f) 445.3 417.9 .9o00

0 •00 f 0 l) .0Pl ... 3.00 1 ?n.?. 1. --- '--- q .4 7.• 3 0- 41.7 0 f 0II .0000 (U0000. 1.00 17765.3U179.4 316.- L 4•;(4.7 417.9 .,0 0

I - 0000 l . 0 000. ?.0n 15 25.23(093.' 4 r? 4 30.5 417. .-9 .V9)01.000W) fo0m011. 3.00 13,--1( .. 1 e.7I 7.h A1#-. 7 t.cý, 375.4 4 17.9 .- t0)0

Figure I NADC Uninstalled Engine Data Input Format (Continued)

2

NADC-79081-60

RALS 3000,1.1 F,',r.j,.,F: 0,N tOF ,,r-2?: '/r- P -" .O,"'.,'CF rl.C,• U 00 0. 6 .()O P5135. 35-4ý-,. ( M31 00 2. PP'i 446.] 4 17 .9 .•y,U0000 o. ?.00 ?34.-43.27]14.4 316.u 2?..0 440.4 417.L* .'Y000

6 ILO-" I_

[•- -- - • ------ - -3 • 00--21 64-.r -1 -€-.-2 5 .,-----,3A.3 -?f.0--2. °-P4.d8 - 3 83-.• .• -- --- .W- 0.-

,I -•O00O . 1.00 23R45.36;-(14.6 316.0 ?.013 493.4 417.9 .9000.2000 n0. 2.00 22096.21733.3 316.0 2.945 43A.1 417.9 .9b00.... . •0O0 - -0. .--- 3 . -?fl? 26.2-0 ( , - .?- -- 3 ]&.-0- -?- . a 7-4---Th1. a-- 4-7-. 9----~. 9bi 0--.4000 0. 1.on ?4?37.387!T3.3 ?lA.1 3.177 485.7 417.9 .1"00

4 .n0 U. ?.nO ???77.29L5•e.'- 31 .1 3.211 431.4 ,]7.9 .b2000S-.4000-- .--... n P.O I ?O1C,.214f 3.5 -316.1-- 3.P42---376.---4-]7.9-.voo)

•000 0. 1.00 25672.4?ý-L4.(, 312-? 3.q73 477.? 417.9 .1'100.6000 0. ?.P0l 233C-7.325-'1.7 31?- . 3.610 424.0 4]7.9 . 'Q0

4 .b(,00 0. 1.00 ?63c, U. 45 e u.U 2L,4.4, 3.FF0 476.6 4] 7. . C)09•t,000 .90 .00 ?-3AP4.35,:51.t- ?94,.,4 3.0?.) 4?3. 5 .1I1.9 .0odt- V.0-00 - -- ) .. . . - ] 7. 17 , ... • , . - 3.cq6 - 36,o.4 - 4 17 . ',-... . 0

].U000 0. 1.00 27644.50101.1 ?73.7 4.?74 4 75.9 -. 17. v, .o91.0000 o. 2.O 24747.303bF,.5 273.7 4.317 422.9 417.9 .,t00

-- . (4D 0O------- - w------ 3 3F-----,----7-]--. ?-7-t4 .- ?77 .7---,-. 3.7 .... * 9- -- ,1-7-. 9--I-5s-o0L,:I.e000 0. 1.00 P9001.5n4.-75.• ?5]9.t l .. 7]-4 474.q 4,17.9 .j eO(I.'e000 0. ?.of0 ?5704..1 ;15; .L, ?L.- .t, ,.7,,r- ?. }.] '.17.9 . 0rO)

• ) ;O u I n Uo .1 1.On 136;--2~t 1?4. h -. 0] 4a '4 410 o0 11) 0000. 2.00 ](3?0.20h41.4 3?4.t 3.0 4+ 45'.50 417.9 .'0o;)0 .. OO- 100 414 - -34.00 IL-U?4. I- - . 3-- -4P -o- 3. n n - -393.7- .]7. .... 9.4•001 10 0110. 1 . 0 0 17 7 7 3 . ?ý 7 . I P . 7 3 . r--7 r-,0 3.? ;; 417 - .7 )

.4•0 0)0 1 O0 U(0 . ? .O0 h 16 33 1. 21 -;;'4 . 0 t P - 4 3.pa ?Q46.5 .1 [.,y 0.; t ) i-- -.400o- IOUO. 13.0t-47..15.- *.3k-.7-... 3,9 .0 -.t17.9- -.- ,- 7.

"• oO0O OU106. 1.00 11-573.310F5.3 31-,.)0 3.6f,'- 496.5 '17.9 .9900" hOU0 1000(0. 2.00 ]6 47.?3 20.? 31-6.0 3.64-4 440.9 4137.9 .'o0)

--. , on -- 0, O to 4 . -- -3.00 15]174 .17>:,;.?•... 3]I,.•_i .•i-.4, z.-7.-3__ _ -10 U000 100 00. 1.00 ?13(1.36( 1e . - 3]-.ec 4 4-,• ',0.] 417.9 .9,7i)o0 •000 1O0 00A. :2.00 1]Lo3 0 0.P77t-" 4 .L, 3]1(-.. 4 . 401 4,26.(-, 4]7.9 .vc it)

6 1Ot. 00 UP4h.-- 3.00- 1-7112.1'4)7-.7 31.1-1 &.4641- 37?.fl n417.9 ..---. o0j1.1U000 10000. 1.00 ?22c99.3 9c.ý,3.4 ?(47 .b 4.cq0b 476.7 417.9 .9j001 .0000 10000. 2.00 ?0604.3u513.t ?Q7. 3 4.,G '423.6 417.9 .9o0)I.u(IOP- 100O",, -- 3.00- -- ?".•? (• p.| _) 7.-,_ .nOn 1. Q. 5 1 7 .Y - .- O1.?'000 )1000f). 1.00 ?(3?0.34 3-17. P73.- t .4?4 475. c .]7.9 .o9tU1. -?000 1OUUO(1. 2.c00 ,1 -.3 > 5.'- ?73.' - . 4 47P?.9 ( ]7.9 .'o 1)1-,' )0() l) 0 q. -3.00 ]•,6c.•,.?3 0(,.7 <273 L. . 3ci. 0 417.9 . 0,J :)

.4000 1C6. 1 .00 137.?0.&-.7 3?7.I 3.?9P 2,55.3 417.9 .9o3 04 o'oUu ?0OUOL. 2.00 11517.15t- 7.! 327.1 3.131 465.6 417.9 .to!9

? Owl70, f.• LI-7.1- . ... h. 7 5 I.?---- -]7-9--3S ....- -• n0 0 20000), . 1.00 134P4..2 5 .5.c 3 ?c.U 3.745 114.? 417.9 .,c', ).b000 200t,00. 2.00 1?PPP.173)0.3 3?c.U 3.7U0 ')46.0 417.9 .',o0-0, 00 20(Of. --. 3.00 A1-1012.125- .9. 91--2.U -3.P31 3Q7,1 417.9-- .• bOO0 2)000 . 1.00 15047.2557H.4 319;i5 'N.3&t C 501.El 417.9 .7,t00

0 0 0 20000. 2.00 13600.19i-17.1 319.5 4. .3( 445.3 417.9 .*oou0 0 .. 000 20 (0 .41. .- 3.0Q -1?06-. 641 -- I -; - 1----31- Q ,'4-- . 47.5- 3ý.t - 4-7.9-- .9oi)

1 .0000 e0uu0. 1.00 17765.30179.4 316.; 3 45 ;4 .7 417.9 .0o001 .OOO e 0( J O9. ?.0 ]) 1595.2 30(;c, -. 1 -) .k ? .- 43@. 5 .17.9 .9o)t)I - U 1) _0 ,0 00.- 3 .Of I-- ]347 ll6t -7-7 . - -'3] .f -.. O e3ý 75.4 -. 17 . - 0:o )

Figure 1 NADC Uninstalled Engine Data Input Format (Continued)

THIS PAGE~ IS BEST QUALITY PRAcT-jC~4rL, f ll,•, CQL Y FURNISHEJ TO DDC

NADC-79081-60

I 1.20U(1 eO000. 1.00 191-P3.34353.7 ?C2.C 6.94 476. F 4 17.9 .y -.o01.2000 20000. 2.00 17f,77.26-??.5 2q9.t 6.3•3 423.7 417.9 .9-dO

- -0 - -- --5- -, . -- -o369-, •-.--47. -ý-- 0---I"1 U000 20000. 1.00 21234.37'.0.b 273.'4 7.0 P0 475.8 417.9 .9b00h|1.4000 20000. 2.00 18711.2864'4.5 273.4 7.nA1 422.Q 417.9 .,YoU0

"I----~~~~~~~~~~~~~ -- 4 0 -0 0 , - -- ,0 - 0 . . 0 0 , - ,-73 .4----7, I , -Sý - 3 a-9• 4---- 74 , -s- -&,-t 4)0 -

1.60UO 20000. 1.00 2?63P.4114.•9 247.7 7.825 474.8 417.9 .o00.IsbOOO 20000. 2.00 I97t.0.31r',5.? 247.7 7.qn4 422.0 417.9 .*o00

<-- ~ ~ ~ a I--?-0)O---0. • -- -• A0%-A7 I,, 2.7•7------ • 4 - 7-• 2 9- - ýý o . --

• 6000 3huM, . 1.00 7159. 12) ' 3.-t 33A. 3 3.773 r57.4 417.9 .Lco0USbOOO 360,'c,. 2.00 -cý,2h. Q-cH.7 330.-3 3.F'?) '93.1 ,17.9 .':LO06b000 360t.. 3.00 '-Pzd-. 6!77.3 330.j 3.874 428.4 417.9 .'•o00

SE!000 3,069 . 1.00 L-?31. 14072 .5 > 329.5 4', . ,5 c39.b 417.9 .'C) 00.8000 3ob0c. 2.u0 7413. -. 1Uh0. 1 32(4.5 b .PA7 471.0 '17.9 ."o00

S'-- ---3-5 0-3 ----- -- - -7-S1 3-3-32 -1-5-7 -9

1.0000 350b9. 1.00 9762.16M:,0.1 32h,.4 5 . 7Q 521.0 417.9 . b0,)

' 1 -00 36089. 2.00 8760.127o6.0 326.4 5-649 461.9 417.9 .9co00I L o 00 PE, 3#,3r14,-7.1 OP-4-3 .-I-- 7-1'7 9-9~O

S1.2o000 360&q. 1.00 11691.IQt-1IU.9 3?1.1 U . r.Q;Q ;01. z,17.v .9c(0QS1 0 ý 0 0 3r, -09. 2.00 10412.15] 5.4 321.0 7.03L 445.4 4)1.9 .' -0i

S ---1 ý 2 0 - 0 U 3 6 ( H 9 , 3. . .3 0 0 - 5 9 1 1 , " -3 . - --7 . 1 1 2I - - 3 A b . 0 4 1] 7 . y -... . . • 0 . . .

L 1.6000 3r'0ý9. 1.00 15P~tf.27112.7 2c-1 .4 10.2 ;4 1 476.5 417.9 . ~0;)I .b 00 350.ht. 2.00 13?917.?Ut- 7o.3 2Q].4 10. ?45 423.4 417.9 .'0o301-nAo00 - 3 0a , - • -nA---11 ~ -�. - - -- -- -- 4 1-,*) -36W. *3- L 1-7--. 9-- -.-. V--

2.000U 3'0•, . .00 176F4.32- ?5.3 ?34.U I?.r-A4 477.1 417.9 .1Co002.0000 3t)O0. 2.00 14F3.24cr44.1 234.U 4?.•-qe? 424.0 417.9 .vC00

b 0 . .. . 0 O -ji -,"A, --- 3b..- --1-eJ.,-,.i- .---- 3.,3 - 3 23 -4 i-? .0 )- - .5-- 1-217--9 ... - --40...

.6000 5 u 0 u 00 . 1.00 3t&1. br't-4.? 330.• t ,774 557.6 '17.9 .- •00• 0 .t 0 '0OQ. 2.00 335!. 4L32., 330.5 3.k30 493.2 417.9 .' ;00Q

-• .. .. & 0 04- q , -t• -(-- P--- .-----3 -A Q 4-P- ,5-.-s Z 1-7-' .9- - ---, .800(0 5'00(0. 1.00 4231. 7?c-4.0 32Q.5 4.;2 540.0 417.9 .•'00

LL 0 10)) 0D O00 . 2.00 3P;,6 . 5572.5 3?Q . t 4 .t-p,7 47R.1 417.9 .V•00------ U4-!-i 0 U40 .----3 * 0 0-f3) . -,F-49, .- -k 29 - b---4. .' 3-- --- 44 -7.9-. c.0-

1-0000 50000. 1 00 5018. 83549.0 326.4 r-.SP0 221.2 417.9 .9b00

1 6 .0000 50000. 2,00 4503. 6573.0 326.4 6r.-0 462.0 417.9 b9b90S -- -I -,-- 04; )-- C-% 0 01 n I•- --- .I- --3 Q5 f-. ---4 7 - 3. .+- --- I P .-( .4-- -5r. -7 ... 1 --3 4 -" . ,?--__ ), ]7- . • - .• .

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: -1.(000 b',(n. 2.00 5355. 7t-14.3 3?1.1 7.043 445 •4 417.9 . :o)0;t - 1.2000 500,- -~3.0O----•65%--5t;.5.s--3?1.1--7.156 388 . 1 417.9 -. 00 0

I .tOO0 50000. 1.00 P164.139".7.7 P)1.b 10,?.C;2 47 6.5 417.9 .YL0o1.6000 5fl(100. 2.00 7162.10(37.9 291.b 10.3c6 423.4 417.9 .9o00

:t...1 -. O0 01 --:i100, 0 .-... -Dn- •'-- -- 0• ,--. F5---? r-4-. /a--- 0, 4 C-i-- - -.-AA .-4--- 1-7-, Y- 74t-)00

2 2.0000 nnu(,o. 1.00 QF1.167-3.5 234.2 ]2.c¶4 177.0 o 17.9 . c0022.0000 50000. 2.00 7',72.1?65.,3 R34.* 1.712 423.9 417.9 .Y 0

i: ....2.-- 0 -- 50 00(0 .--- 3 .---- •6 4. -- - 2•--- 3-4.2-- f; P 9- -3-36 - -- .4 17. ... 9 .0--

2 ?.20000 500)00. 1.00 9336.17(-46., 2?04.2 13.?P0 4 3.P 417.9 .'(j 00

2 .LO000 5000n. 2.00 79%8.13317.5 204.2 13.390 429.8 417.9 .9b0U3 C000 - , -,0----7,--oQ 6.57- -0z- ?-13. -- 74.F- 471 .•o---

Figure 1 NADC Uninstalled Engine Data Input Format (Concluded)

,i :rL 10p. 'i UD ST QUAJLITY Ty 1 C I[ jAi• ........... ., ;:.!j]iD I(DDC ....

NADC-79081-60

columnns 8 and 9 respectively, are input in square inches for the

NADC input instead of in square feet as in the Air Force version of

the PIPSI code. The square inches are converted internally (in the

revised code) to square feet.

(2) The association of external file names to internal program tape

definitions is done with GET statements rather than ATTACH

statements. For instance,

use GET,TAPEI=AFE to connect TAPEl with previously stored AFE

(Uninstalled engine input data file).

also, GET,TAPE51 = inlet file

GET,TAPES? = altbody file

GET,TAPE53 = CFG file

GET,TAPE54 = capture area file

(3) The code was modified to automatically generate installed

propulsion system perforwrance output data for use in mission

performance calculations. This data is written to an output file

named TAPE7. This file is automatically qenerated with each

expcution of the PIPS[ program. The format for the TAPE7 output is

as shown in Figure 2. The format was provided by NADC at the start

of the contract work.

The modifications, debugging, checkout, sample calculations, and

demonstration were all performed using the NADC computer system. At the

4 P' i

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NADC-79081-60

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NADC-79081-60

beginning of the contract, a magnetic tape containing the existing Air

Force versions of the source codes for the PIPSI and DERIVP plus a

complete library file of inlet performance, nozzle/aftbody drag maps, and

nozzle CFG maps was mailed to NADC and was installed by NADC

personnel as permanent files in their CDC computer system. The

modifications were then accomplished by Boeing personnel using a remote

access keyboard terminal located at Seattle, Washington.

Preparation of ADEN Nozzle Maps

A set of nozzle/aftbody drag and CFG maps for the ADEN CD Nozzle was

developed for use (luring the installed performance calculations. These

maps for the ADEN configuration are described and shown in Appendix A.

Calculation of Installed Performance

After the source code was modified, binary (object) deck files were

created and stored as permanent files in the NADC computer. After the

modified object decks were obtained, a series of installed performance

calculations was performed using the matrix of engines, inlets,

nozzle/aftbody drag maps, and nozzle CFG maps described in

Appendix A. Plotted results from some of the installed performance

calculations are contained in Appendix A. Appendix A also contains a

catalog of the files stored in the NADC computer with key files indicated.

Demonstration and Training Session

At the conclusion of the contract work, a training session was held at

NADC to explain and demonstrate the operation of the computer programs to

7

NADC-79081-60

NADC personnel. Appendix B contains some of the general briefing charts

that were contained in handout material distributed to the NADC personnel

who participated in the training sessions. The charts are presented in

Appendix B to provide a source of information for those who want to learn

of the general operating characteristics of the computer programs without

obtaining the complete set of documents describing the programs

(References 1 through 4).

8 0 a

NADC-79081-60

APPENDIX A

INSTALLED PERFORMANCE CALCULATIONS

9

9 I

NADC-79081 -60

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100

NADC-79081-60

TABLE A-Il

SUMMARY OF INLET CAPTURE AREAS

INLET ENG. T2 A0 Ac'INLT -1-p •-A FT2

CONFIG. MACH ALT. TYPE T2 PTo c

.80 50000. T/F 330. .98 .74 9.183

F8 .80 50000. T/J 284. .98 .74 7.903

.60 50000. T/F 331. .967 .975 7.882

NS .60 50000. T/J 284. .967 .977 6.763

.80 50000. T/F 330. .982 .95 7.168

NS2 .80 50000. T/J 284. .982 .95 6.169

.80 50000. T/F 330. .965 .77 8.690

LWF .80 50000. T/J 284. .965 .77 7.479

2.00 50000. T/F 234. .925 .915 8.079

ATS2 1.60 50000. T/J 256. .948 .872 7.042

11

NADC-79081-60

400

300 , , -_

200

100

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8

M0

Figure A.1. Maximum Engine Airflow for Turbofan Enfqine

400

300

200

100

00 0.4 0.8 1.2 1.6 2.0 2.4 2.8

M 0

Figure A -2. Maximum Engine A irflow for Turbojet Engine

12

-r ii

NADC-79081-60

20 _

18 -

6 Altitude: LATS2

16-50.000 tt{ ---1 --

SLWF

WFNS NS2

(Ib/h x 10 ) 3

I" II I . _

10 1- -_

2 4 6 8 10 12 14FNA (2b x 10-3

Figure A-3. Comparison of Installed Performance for Various InletConfigurations at Mach 2.0 (Turbofan Engine)

13

NADC-79081-60

18 .

*Altitude: I36,089 ft

INS, NS2 ,

t14 LWFATS,F8

12

WF

(Ob/h x 10-31

I I

1101

4

0 2 4 6 8• 10 12 14

FNA (lb x 10-3)

Figure A-4. Comparison of Installed Performance for Various InletConfigurations at Mach 0.80 (Turbofan Engine)

14j

* ~NADC-79081 -60

eMaximum power setting

1.00 - - - - - - - - - ~ - _ _ _

P 0.80 4---

0.7 ________ ______1 ___________________ NS 'NS2 LWVF 1

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8

Figure A5.5 Cornpirison of Matched Inlet Total Pressure Recoveryfor Various Inlers (Turbofan Engine)

0.0eMaximum power setting! S ,V

0.20

0.10.

Figure A -6. Comparison of Matched Inlet Drag for Various Inlet(Turbo fan Engine)

15

NADC-79081-60

30___ _

FNMAX

( Ib x 1 0 '3 ) 2 0 1 --

10 - . . . . A TS2 . . . .I I • _. • F8 .

i • •LWF0 _ 'l "• NS NS2 [.0 04 0.8 1.2 1.6 2.0 2.4 2.8

M 0

Figure A .7. Comparison of Maximum Installed Thrust for Variou.5 hfletý(Turbofan Engine)

30 . -- -- -

I I

FNINT

fib 103

ATS2

0 0.4 U.d 1.2 1.6 2.0 2.4 2.8

M 0

Figure A-8. Coin parison of Intermediat,' Installed Thrust for VariousInlets (Turbofan Engine)

16 0

==~

NADC-79081-60

0 0.40

00 Maximum power setting

0.30

CD0 20________

0.10 /

I • SPILLAGE

04 0.8 1.2 1.6 2.0 2.4 2.8m 0

Figure A -9. Inlet Drag for a Normal Shock Inlet With a Turbofan Engine

0.40- -0 ATS2 inlet

0 Maximum power setting

0.30

CD

0.20

0 0,4 0,8 1.2 .1 k2.0 2.4 2.80

Figure A,.10. Inlet Drag for a Mach 2.0 Inlet With a Turbo/an Engine

17

NADC-79081-60

0 .40___ ____

S*ATS2 inlet

OAltitude: 50,000 It030• M0: 2.0

0.30O__ ____ __

CDINLET

0.20

0.10 -

BYPASS -BYPASS

BLEED SPILL

10 8 6 4 2 0 -2 -4PS

Figure A. 11. Inlet Drag Versus Power Setting for a Mach 2 InletWith a Turbofan Engine

18

=I

* NADC-79081-60

40 _ -

36

*Altitude;50,000 fi

32

F8 ATS221824 ___ ~LWFI _I-244

F NS(tb /h 1 0 -3 1 o/. .. ..

I I20NS

12 -- --

-_ -

1 0 4" - 12 Ib 16 20 24 28

F -3

SFNA (1b x 10"3

Fiqure A. 12. Comparison of Installed Performance for Various Idlet

Co•diqurations at Mach 2.0 (Turbojet Engine)

t 4- 19

NADC-79081-60

40

36

32* Altitude :

36,089 ft

28

24--

WFNS, LWF ATS2, F8, NS2(Ibih x 10"3)

20 . .. ... .. .. .

I I

18 . . . . .. . .. . .. . .. . . .1

0 4 8 12 16 20 24 28FNA (b x 10-3)

Figure A. 13. Corrmperison of Installed Performance for Various InletConfigurations at Mach 0.80 (Turbojet Engine)

20

NADC-79081-60

setti ng

100

PT, 0.90 .ATS2 i

2

0.80 _ _ ._

0.70NS2 \N LWFI

0 04 0.8 1.2 1.6 2.0 2.4 2.8

M0

Figure A. 14. Comparison of Matched Inlet Total Pressure Recovery

for Various Inlets (Turbojet Engine)

LWF0.40r NS NS2

9 Maximumpowersetting0 .3 0 ----- ---.. .

0.30- F8

o.2o . . .... ...... . . .. . . .--

COINL

0.10 .... .... ...

. ATS21..1 _ __ _ _ __ ___ __ ___ __

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8

,I M 0

Figure A- 15. Comparison of Matched Inlet Drag for Various Inlets(Turbojet Engine)

21'5

NADC-79081-60

FNMAx 20

(lb x 103) ATS2

10 ______LWF Z, "'•NS2

00 0.4 0 .B 1.2 1.6 2.0 2.4 2.8M 0

F.qure A- 16. Comparison of Maximum Installed Thrust for Various Inlets(Turbojet Engine)

30

FNINT 20

(Ib x 10-3

Mo

Figure A. 17. Cofnparison of Interrnediatc Installed Thrust for VariousIn lets (Turbojet Engine)

22 SM 0

NADC-79081-60

0.40

04Maximum power setting

0.30

CD020

010

SPILLAGE

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8Mo0

Figure A- 18. Inlet Drag for a Normal Shock Inlet With a Turbojet Engine

0.40r0 ATS2

inlet

* Maximum power setting

0.30 -

0.20

0.10o

SPILL

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8Mo

Figure A- 19. Inlet Drag for a Mach 2.0 Inlet With a Turbojet Engine

23

NADC-79081-60

0.40

* ATS2 inlet* Altitude: 50,000 ft

MO: 2.0

0.30 _

CDINLET

0.20 __

0.10

BYPASS

_BLEED _ SPILL

10 86 4 0 -2 4

PS

Figure A-20. Inlet Drag Versus Power Setting for a Mach 2.0 InletWith a Turbojet Engine

24

F NADC-79081-60

CýATALOG OF E-0'3293 'c~9 12. 54. (1

FILE tiA1E(S.

RiC If31 AC;it'M3 AtiENC:I' FI HA ATSTFDM FITcTFW FiTE$TFWMAiTSTJr' FITS~Tjtg FITSTJW ATSTJWM ATSE FiTSaIM- P EILOUTBOEING1 POEINGE BOtNGTJt' BflHGTJW CVAI)EN C.UADEN2 C:VlC V211 C V21)I c.UarI6 EtAGI'EIM FE: Fc:TFDi FE:TF1+1FE:TFI. FE:Tfl-l1 FSTF1411 FE;TrwaE F6'TFW--' FE:TFmr.17 FE:TF1.J4FE:TFW4M FE: TJt F6T-lt'M FETJW FE;TJWM LWF L.L.iFT FrFL14FTF14-1 LW-FTFW LWFTFWM- LWFTJr' LWFTJDPI LWFT-11 LWFTJWr1-fl1FiP>4:1 1*19SLUE: [4At'C.' r4IAE'CZ3 tiADC4 11AtIC41. rHADC:7?tiAI'C2't: NFIrC'CE:F 1-iric9B N S (iSTFri HS TFI'ri1 rST41tiETF;*1 rV=sTJD iT-rl HSTiE'rW HST1-J r1:E.TqIE'JI*c*H* rt IaT F :rti5' :TFL'-1H E'rl-aFiw liSsTFI'JIt1 riSET.Ir' 11cisar1 tnt .L Qsa 41WHLUTEEST rU I- AUE DF 1 N(..'t'FE. HUIETO T A 'E-. TE'STOLITUScEF.: LJFABF1' WPi:Sri281TTY

F. FILEES(S)

READ',~

3FILE NAME FILE CONTENTS

BOEING1 Dry Turbofan Engine Uninstalled Data

BOEING2 Afterburning Turbofan Engine Uninstalled Data

BONGTJD Dry Turbojet Engine Uninstalled Data

£BONGTJW Afterburning Turbojet Engine Uninstalled Data

NADC7 Source Deck for PEPSI Program

NADC9B Object Deck for PEPSI Program

WPABDP Source Deck for Derivative Process Program

WPABDPB Object Deck for Derivative Process Program

MAPXI Library File of Inlet, Nozzle/Aftbody Drag,and Nozzle CF Maps

* G

CVADEN ADEN Nozzle CF MapFG

ADENCD Nozzle/Aftbody Drag Map for ADEN Nczzle

Figure A-21 Catalog of Permanent Files on NADC Computer Account

25

NADC-79081-60

40

~30A101A9

4O

w

,2.2

z 0

n-103"3

~~ .2t _ _3 _ _ _

5.00

0340 360 380 400 420 440 460 480 500

STATION (INCHES)

Figure A -22. Nozzle and A ftbody Area Distribution for a TwinADEN Nozzle Configuration

26

NADC-79081-60

0.28

0.24 - -

A10 /A9

-- 5.000 .1 6 -. . .

CDOAB 3.331

2.502,27

I . . . .. . . - ] 4

0.04 0I

0 0.4 0.8 1.2 1.6 2.0 2.4 2.8M0 -

Figure A -23. Drag for a Twin ADEN Nozzle Configuration

27

NADC-79081-60

1.00

0.99_____ _

INTERMEDIATE

0.98 _..

CFG MAXIMUM

AFTERBURNING

0.97

0.96 . . .. .

0.95 . . ..0 2 4 6 8 10 12 14

PT 8/Po

Figure A-24. Gross Thrust Coefficient for an ADEN Nozzle Configuration

28

NADC-79031-60

APPENDIX B

GENERAL COMPUTER PROGRAM OPERATING CHARACTERISTICS

29

NADC- 79081-60

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REFEREN•CES

1. Ball, W. H., and Hickcox, T. E., Rapid Evaluation of PropulsionSystem Effects, Volume I - Final Report, AFFDL-TR-78-91, Vol. I,Air Force Flight Dynamics Laboratory, Air Force Systems Command,Wright-Patterson Air Force Base, Ohio 45433, July 1978.

2. Ball, W. H., and Atkins, R. A., Jr., Rapid Evaluation of PropulsionI, System Effects, Volume II - PIPSI Users Manual, AFFDL-TR-78-91,"Vol. II, Air Force Flight Dynamics Laboratory, Air Force SystemsCommand, Wright-Patterson Air Force Base, Ohio, 45433, July 1978.

3. Hickcox, T. E., Atkins, R. A. Jr., and Ball, W. H., RapidEvaluation of Propulsion System Effects, Volume III - Derivative

' PProcedure (DERIVP) Users Manual, AFDL-TR-78-91, Vol. III, Air ForceFlight Dynamics Laboratory, Air Force Systems Ctmrnand,Wright-Patterson Air Force Base, Ohio, 45433, July 1978.

4. Ball, W. H., Rapid Evaluation of Propulsion Svstem Effects, VolumeIV - Library of Configurations and Performance Maps,

0 eAFFDL-TR-78-91, Volume IV, Air Force Flight Dynamics Laboratory,Air Force Systems Command, Wright-Patterson Air Fz.rce Base, Ohio,45433, July 1978.

I

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PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM … · 2011. 5. 14. · REPORT NADC-79081-60 S\WI OF PIPSI/NAVY-RAPID EVALUATION OF PROPUL-SION SYSTEM EFFECTS FOR TWilL NAVY GAS