unclassified ad number - dtic · inriine.rino dosrri, ptionw, equations, and flow charts are...
TRANSCRIPT
UNCLASSIFIED
AD NUMBER
AD907815
NEW LIMITATION CHANGE
TOApproved for public release, distributionunlimited
FROMDistribution authorized to U.S. Gov't.agencies only; Test and Evaluation; 29 DEC1972. Other requests shall be referred toAir Force Flight Dynmaics Laboratory,Attn: PTB, Wright-Patterson AFB, OH 45433.
AUTHORITY
AFWAL ltr, 11 Feb 1980
THIS PAGE IS UNCLASSIFIED
AFFDL-TR-72-147 - VOL. II
0,
PROPULSION SYSTEMINSTALLATION CORRECTIONS
VOLUME SI:PROGRAMMERS MANUAL
D D-W.1.AL T. B
THE BOEING COMPANY
TECHNICAL REPORT AFFDL-TR-72-147 - VOL IIDECEMBER 1972
Distdbuvim *Amusd to U.S. Oownmmnt sgowss op*V;""t ed evelueion; "&I ^t asope 3 Oseembw 1012.Other r"queM fmo tNiS do•.,, must be reterred to AirForce Flight Dynamics Labotatorv (PT@), Wrisht.PonnermnAir Force lee, Ohio 45433
AIR FORCE FLIGHT DYNAMICS LABCRATORY
AIR FORCE SYSTEMS COMMAND
WRIGHT-PATTERSON AIR FORCE BASE, OHIO 45433
BestAvai~lable
Copy
m )
NOTICE
When Government drawings, specifications. or other dataare used for any purpose other than in connection with adefinitely related Government procurement operation, theUnited States Government thereby incurs no responsibilitynor any obligation whatsoever; and the fact that theGovernment may have formulated, furnished, or in any waysupplieac the said drawings, specifications, or other data,is not to be regarded by implication or otherwise as in any
Smanner licensing the holder or any other person or corpora-tion, or conveying any rights or permission to manufacture,use, or sell any patented invention that may in any way berelated hereto.
|I
Copies of this report should not be returned unless return
is required by secirity considerations, contractual obliga-tions, or notice on a specific document.
PROPULSION SYSTEMINSTALLATION CORRECTIONS
VOLUME I1:
PROGRAMMERS MANUAL
W. H. BALL
Distribution limited to U.S. (;.over 111nt111 t Oy01w5.I 4ily,test nrmd evaluation, statlonimnt dpmplmd 29 L)Documbe, 1972
Other requests foa th1S domHAIMmmem Musm b0 1m00118Omd to Air
Famore Flight Dy nammmks Ldtboratory v P1 W ), Wriht- t t',ettrsUto
Air Force Base, Ohio 45433
FOREWORD
This report was prepared by the Research and EngineeringDivision, Aerospace Group, of The Boeing Company underAir Force Contract F33615-72-C-1580, "Propulsion SystemInstallation Corrections", Project 1366. The program wasconLucted under the direction of the Prototype Division,Air Force Flight Dynamics Laboratory, Air Force SystemsCommand. Mr. Gordon Tamplin was the Air Force ProgramMonitor.
The program was initiated on 31 December 1971 and draftcopies of the final reports were submitted for approvalon 31 October 1972.
Dr. P. A. Ross was Program Manager and Mr. W. H. Ballwas principal investigator during the program. Significantcontributions to the program were made by the followingIndividualsr Mr. Joe Zeeben, engine performance; Dr. FranklinMarshall, irniet and exhaust system technolegy; Mr. John Petit,nozzle internal performance and nozzle/afterbody drag; andMr. Gary Shurtleff, progrp.mming.
This report contains no classified information extractedfrom other tiasified reports.
Publicati•c, c! this report does not constitute Air Forceapproval ',,e report's findings or conclusions. It ispublisho- - for the exchange and stimulation of ideas.
Lt. Col. Ernest J. Cross, Jr.Chief, Prototype DivisionAir Force Flight Dynamics Laboratory
Ui
ABSTRACT
This report prescnts the result:; of a research progra. todevelop a procedure for calculati.nc; TropulIsion :;y,;tem in-stallation losses. These los;as iacludo inlet and Jiizzl,internal losses and vxternal drag ]ocses for a wide variet'yof subsonic and supersonic ai'crcrft confiqurationz; up toMach 4.5. The calculation procedure., which was lrgelydeveloped from existing engineer infj raedur,.,(tn(I *ý:xoo:ri-.mental data, is suitable for preliminar, ';tuudios ofadvanced aircraft conficturatolon;. inriine.rino dosrri, ptionW,equations, and flow charts are provided to heir) in adarthe calculation procedures to d(IitiI c(-ir:,utLer ro'lt nI:;.Many of the calculation procedures hav,, already 1beern pr,ýor ivAon the CDC 6600 compuLtr. Proqram Hi.,stjn,i-. .;nd f111.1 Y.h,-tare provided for the calcul.ition prcodurenr tLat,. i-wiv, heenprogrammed. Tho work accomp]i Thed Iurinri th- nr,.,I, 1,1tained in four separate volumc,;. Vol:ume I contain, -inengineering description of th, calci]fati,, rrlrocr,,roe;.Volume II is a proqrainerl's ma:nual (,ontainiinq flow.; :rt,listings, and subrouti ne dusc riptLion;. Vulim,11 ILI ,Contitin.sample calculations and saimno],2 ilnput data. VOl u.",. IV c.'n-tains i )okkeep.ing definitions and data eorrelatin.;.
C
01i
TABLE OF CONTENTS
SECTION Page
GENERAL DESCRIPTION OF COMPUTER PROGRAM 1II DESCRIPTIONS OF SUBROUTINES AND LISTINGS 5
MAIN PROGRAM (TEM 333) 5
COMPUTE 13
TABIN 21
INLDRAG 26
SIZINL 31
AIRBYP 35
AIRSPL 43
DRG 47
CDCONV 34
PLUGMX 60
PLUGNM 64
ABINPT 68
SUBBT 72
SUPBT 78
DRAGAB 82
DBOATR 88
CABTAB 92
DINTFR 97
DBASER 101
DBTTB 105
/ v
TABLE OF CONTENTS (Continued)
SECTION Page
FIXDIM 107
ATHOS 110
PERF 114
OUTGO 118
WARNING 122
STORE 125
CHKRP 128
GTHRST 131
DATA 137
PLACIN 140
TABL 1 143
TABL 2 146
TABL 3 150
TABL 22 154
DSCRUB 157
III DESCRIPTION OF FUNCTIONS AND LISTINGS 167
AREA 167
HOFT 171
TOFH 173
PROFH 175
HOFPR 177
COFH 180
COFHS 2.3
vi
TABLE OF CONTENTS (Continued)
S
SECTIONPage
KOU14T 186
| DEMAND 189
AREAF 192
AUXHST 194
*IV CROSS LISTING OF PROGRAM TEM 333 196V INLET MAP PROGRAM
205
(
q" vii
LIST OF ILUSTRATIONS
Figure No. Title Page
1 Flow Chart for Program TEN 333 6
2 Flow Chart for Subroutine COMPUTE 14
3 Flow Chart for Subroutine INLDRAG 27
4 Flow Chart for Subroutine SIZINL 32
5 Flow Chart for Subroutine AIRBYP 36
6 Flow Chart for Subroutine AIRSPL 44
7 Flow Chart for Subroutine DRG 48
8 Flow Chart for Subroutine CDCONV 55
9 Flow Chart for Subroutine PLUGMX 61
10 Flow Chart for Subroutine PLUGNM 65
11 Flow Chart for Subroutine SUBBT 73
12 Flow Chart for Subroutine SUPBT 79
13 Flow Chart for :Subroutine DRAGAB 84
14 Flow Chart for Subroutine DBOATR 89
15 Flow Chart for Subroutine CABTAB 93
16 Flow Chart for Subroutine DINTFR 98
17 Flow Chart for Subroutine DBASER 102
18 Flow Chart for Subroutine ATMOS i11
19 Flow Chart for Subroutine PERF 115
20 Flow Chart for Subroutine GTHRST 133
viii
SUMDOLS A .NOMENCLATURE
Aiea, in2
Ac Inlet capture area, in2
( AO Local stream tube area ahead of the inlet, in2
AO Free-stream tube area of air • inering the inlet, in2
at Aspect ratio, dimensionless
B Velocl.tj decay exponent, dimensionless
C Sonic velocity, ft/sec.
CE Drag coefficient, D , dimensionlessC q4AREF
C-D Convergent-divergent
CD Additive drag coefficient,CD CDADD , dim n-ionlessDADD ~AD!)m A
CD Aftorbody drag coefficient,- 2 A, Pifens,,JoI•i•isC VAX Base drag coefficient (PbP"I)ABASE- climensionl_.ss
CDBase ,AX
CD Scrubbing drag coefficient, DRAG ' dimensionl.-s
FCf Thrust coefficient, • , dimensionless
g -cpl
Stream thrust coefficient, di.onsionlcs.,(Cs (defined by Figure 48 of Volume IV)
CV Nozzle velocity coefficient, dimensionless
Cony. Convergent
D Drag, lb.; Hydraulic Diameter,_!A # in., di.-%mrtr, Il.
ix
SI DOLS AND NOMENCLATURE (Continued)
F Thrust, lb.
F Ideal gross thrust (fully expanded), lb.
f/a Fuel/air ratio, dimensionless
g Gravitational constant, ft/sec2
h Enthalpy per unit mass, BTU/Ib.; height, in.
hfan Enthalpy of fan discharge flow, BTU/lb
hpri /nthalpy of primary exhaust flow after heat additionpri 8TU/lb
ht Throat height, in 2
K Velocity decay coofficient, dimensionless
L Length, in.
H Mach number, dimensionless
P Pressure, lb/in2
P r Relative pressure; the ratio of the pressures paand pb corresponding to the temperatures Ta and 7respectively, along a given isentrope, dimension!..:s-,-
P T Total pressure, lb/in2
Q Effective heating value of fuel, BTU/Ib.
q Dynamic pressure, lb/in2
R, r Radius, in.
S Nozzle centerline spacing, in.
T Temperature, OR
V Velocity, ft/sec
X
SMBOLS AND NOMENCLATURE (Continued)
W Mass flow, lb/sec
WBX ,Bleed air removed from engine, lb/sec.
W, W V" Corrected airflow, lb/sec.
Wf Weight flow rate of fuel, lb/sec.
SW 2 Weight flow rate of air, primary plussecondary, lb/soc.
W Primary nozzle airflow rate, lb/sec.
x Length, in.
a Angle of attack; convergence angle of nozzle, degrees
y Ratio of specific heats, dimensionlessSAP T
C Diffuser loss coefficient, , dimensionless
Burner efficic'ncy, dimensionless
V Kinematic viscosity, ft 2 /sec.
p Density, lb/ft 3
SUBSCRIPTS
B Burner
b, base Base flow region
BP Bypass
BLC Boundary layer bleed
btail Boattail
c Core (nozzle); capture (inlet)
DES Design conditions
xi
SYNBOWX MAND NftMENLATURE (Continued)
SUBCRIPTSe Boattail trailing edge
EFF Based on effective area
ENG Refers to engine demand
f Fuel
g gross
GEOM Based on geometric area
int Interference; internal
ip Ideal, primary exhaust flow
Jet Exhaust flow jet
max Maximum
min Minimum
s Scrubbing flow region
SPILL Spillage
T Total condition; throat station
tf Total condition, fan flow
T/O Takeoff
t p Total condition, primary flow
o Local conditions ahead of inlet
2 Compressor face station
8 Nozzle throat station
9 Nozzle exit station
18 Fan discharge throat station
Free-stream condition
x Local
SECTION I
GENERAL DESCRIPTION OF COMPUTER PROGRAM
The engine installation calculation procedure naturallybreaks into three divisions: inlet, engine, and nozzle/afterbody. Each of these divisions is represented inTEM-333 by a set of subprograms logically subordinate to amonitoring subprogram which functions as a quasi-mainprogram for that set. The term module will be used todesignate a quasi-main and its subordinate programs. Further,within a module procedures are subprogrammed to isolate theprocedures from one another and to isolate logical dirictionpi gramming from computational programming. The benefitsof this organizction are threefold. First, checkout. Eachmodule caa be checked out independently of the others. Secondly,logical simplicity. The logical structure of the programas a whole is more apparent. Individudl subprograms aresimpler; being small with a limited p.,Arpose. Finally, easeof modification. Engine installation programs are constantlyundergoing modification so the ability to attach and detachnew modules or procedures quickly is a necessiiy. The smallsubprogram-module arrangement allows for quick change sincethe connection to the next level is more apparent.
The modules are tied together by subroutine COMPUTE whichcalculates the installed performance for a single uninstalledperformance point. The main program, TEM-333, handles callsto the input routines, then reads the uninstalled performance
( points one-by-one; calling COMPUTE for each, outputting datawhen required until the last point has been computed.
Programs included in T&L1-333 and their purposes are:
TEM-333 - Main Program, monitors program logic
CO4PUTE - Controls calculation of a performance point
Inlet Module
TABIN - Reads Inlet Input Deck
INLDRAG - Monitors Inlet Drag Computation
AIRBYP - Computes External-Compression Mode
(I
AIRSPL - Computes Mixed Compression Mode
SIZINL - Computes Inlet Capture Area
DEMAND - Computes Engine Demand
AREAF - Computes F1 where A F
Afterbody Module
ABINPT - Reads Nozzle Input Deck
DRAGAB - Monitors Afterbody Drag CaLculations
DINTFR - Computes No~zle Interference Drag
DB0ATR - Monitors Boattall Draq Computdt ion
DBASER - Computes Base Drag
DBTTB - Computes CDBT = f(M, PS)
CDC0NV - Monitors C-D Nozzle Boattail Computation
PLUGMX - Computes Boattail Drag for Plug Nozzle,Mixed Flow
PLUGNM - Computes Boattail Drag for Plug Nozzle,Non-mixed Flow
DRG - Computes Boattail Drag for C-D Nozzle
SUBBT - Computes Subsonic CDBT for C-D Nozzle
SUPET - Computes Supersonic CDBT for C-D Nozzle
CABTAB - ComputesCDBT as Function of A1 0 /A 9
AEXHST - Computes Nozzle Exit Area
Engine Module
PERF - Computes Gross Thrust
CHKRP - Computes Thermodynamic Properties atThroat
2J
SGYfhStT - Performance of Propulsive
Nozzles
; NiW T - Computes Enthalpy Given Teimperature
T011 - Computes Temperature GivtmEnthalpy
PROFH - Computes Relative Pressure Given Enthalpy
t HOPFPR - Computes Enthalpy Given Relative Pressurv
C0FH - Computes Critical Velocity Given TotalEnthalpy
C0FHT - Computes Critical Velocity Given Static* Enthalpy
Miscellaneous Programs
STORE - Stores results of a performance point.
OUTGO - Outputs an engine performance matrix
WARNING - Prints warning message heading
FIXDIM - Determine dimensions of A8 and A9 input
ATM0S - Computes atmospheric data
DATA - Transfers and output input card images
Tabular Input Programs
C TABLl - Inputs table format 1 tables
TABL2 - Inputs table format 2Q tables
TABL22 - Inputs table format 2K tables
TABL3 - Inputs table format 3 tables
PLACIN - Reads a tabular array
K0UNT - Counts non-blank input fields
Linear Interpolation Programs
TABUl - Interpolates F - f(x)
TABU2 - Interpolates F - f(x~y)
3
TABU3 - Interpolates F = f(x,yz)
• IFIND - Finds Interpolation Interval
FACINT - Computes Interpolation Factor
CVINT - Perform Linear Interpolation Calculation
4
4F
SECTION I11
DESCRIPTIONS OF SUBROUTINES AND LISTINGS
SUBJECT: PROGRAM T1M-333
PURPOSE: Main Program TEM-333 monitors the overallprogram logic.
METHOD: All supporting data is input, then the programreads performance points one by one, computesand stores the results, and outputs an arrayof results whenever Mach or altitude changes.
USAGE: PROGRAM TEM333 (INPUT, OUTPUT, TAPE5, TAPE6 =
4UTPUT, TAPE1 = INPUT)
tNPUT or TAPE1 System Input
OUTPUT or TAPE6 System output
TAPE5 Card Images of Input
TAPE7 MARK II output
SUBPROGRAMS: ABINPT DATA FIXDIM
OUTGO STORE TABIN
TABLI TABL2
(!
C5
WRTLL DATA CARD IM4ESOkiUJ ,FILE AND on TAPE 5
IREAD andWRITtETITLE
READ ENGINE BLEED TABLE
READ REERNLET NOZZT DRATADC
(CALL TABINI
EAD :A
CREAD AFTERSODY INPUT DATA DECK
F SuET 1: FL SOW CH ART FOR PRGAM AND X~
6
rý
Ir
L
OF ARRAY FOR LAST
YS MAC H - ALTICALL OUTGOI
CSTO
DCARD IMAA CA
FE ROR • • O
ONVRT.S |ST
AO
ARRAY FOR FDTA
YES Q2 I YES '-.MACH - ALT
REA URE
CARD NO
READ PERFORMANCE- mm -- mm m~mm POINT DATA
CARD IMAGE
CONVERT All F CP AR3INPUT FIELDS TO AllAND A9 90 INCHES, OF
• REQUIRED
I-- -SFC FN
S~~Figul~r: FLOW CHART FOR PROGRAM TEN 333 (Cwtl)
/7
PRINT OUTPUT NO ALT-MACH POINTS.Nw YS ARRAY FOR LAST NALT~ 1
ALTIUDEMACHALTSAVE ALTITUDE
INCREMENTNO. OF ALT-MACH
.
ATEX CASEEN
ACH-10
Fi ur TE FL W C A T F R P O RMIE
3 C n l d d
?8
0 000
0000 U
00
00 0
00 IL
00I
0088cc,
000 000~0I
000000
00 ej00a .I-
M ra 4 P er 1Li0 In 4 1
B00 w re
00 * 0 0 aUC3~ 4 a 0Z 0 1 .3s1
88 Z ZP az -4 zz00 I ~ ~ ~ ~ 0- 1.W4gQIJ - 64U~
ac * 00.004d~-~ggl
1 :% ~ s 1
000 A
00 Z UfI%0 IO Z0J4 aaf- .P 2 IJ4 0 I
0l.Z !4~ %1 --. 4J ~ ii( ~ ~ 0 1 (
coZ IN.,%.U 2 j2% i~% i. a0 -oo 0I014it 1. 4 %41 I'I % % N4- 4* % . .
00 11"- 2 C0Il0000 0.0-~ ~ ~ t44
d'4
'--
00 .il a., WIC0~ ~O*''C~L I) '.Uh-~
00 Wt6 (A
cc I Poo U Z
0 0
00
0000 00 0
0.000I
00
00
00I
0000
00 j
00I
00'
00!00 .
00-
R-
00 on 4 % 0 s.4f. " I
001 0 0 4 4f ,Y 4NW0 0 g 1 1 4 X" 4 11 0 a. 1 2 - 4 11 'e*a -I w w wefr w ofo I yW etyY(00 00 00000 .3 *3 1 3nn(' j a,' i0
$.-1 04 04P 4C00 -. JUcc . . ~ *% - 4*
co* 4-
00 2- U0 . U.-e'.
00, - I2* *2-00 8.0m4 .3Z 4AU4I -co W I.. at-B~-4 - . 24 0fcc Z 4.4V0.% sU d .400 "" a
0c 10 0 A0 0u Al0!0'-z z 10; . % (%Z * 3 c % ~ i- ~ . .
00 U -..0Z ~ r00 000 'x '.x
%N0., w I4.) JUUIIUO
%. 0.2 "0).I 2 a 1.4 U. I.)M 0.
'9. a2 ' -A 1) 11 0- .'11 1
cc A 3121JJ~l~0' ZI142~*'9J1~1,4 me,,.r ,V)If z0~ ~ O 9 O ' ' Q 0 0 O,''~00o $4L~ 49202a)111Ja,11- dju.0j T*I.jJjri
a ý' 1 4& 19
Ix a
* .I4
le I
I IZ * 11 :t eA
4'4-
(I~ uI1 % .u , :
49 of 4NN
CS VI .
9242Lv o f y ft I
.4 ev C 3 II' #% 1 1 0, 2'2'
I j 0 4 1 w .
f4 on P% -
Mi P,.4 f"IL A u0lU 0 s. 00.1 0 .4 m k00 MA t .4
'0UN0I" 44P~Y -01 -# 2 1U : 0a 4 44 4v s a
13C t m42 M 1 i14 jZ:2 1 to " S.2 sit 43.2 t2
00 L. 0 aq C; It 10 o.
fy Ic Ia (.9 a N m .Nl fi. N. fSO Zo us (3
m0 Jon UA 00'0 Oi 0 *. C . 43OIS: I0 4 .4 .4. f94 04)dis e
'A. 'a f K11 1 .Al' 000 . 0 0m 040L3 u C2. S It.~ r
Aj4. inN ".44"s %
ff99."99. .. 12 -to' .213 13 as8.%,t 'Cis aA Il 3 Co # #A ( 3 0 C 411,S4 .2 0 SanrQrIP r1,,~ t3 p
6.26 T II IV'It.3 . T b.el w 1'll0
sill 1. 3 , A l4 aAa -4*9 .14A -4 a 41*A.I%* -4. 1-,-4' w 4.... Is-5 K~v A- 0 tA ` .cjZ.1 a
IAA. ~ ~ it Z-'~ S .4.3;, '~.4t .4.4 A35t1,.
"'4f 4 n NONA" 4 Is is mU "0 b t - f . * f.1 , !I S - s, s- `
("Az u PV , 0 U 3 t m f' 11 J-s -f~3Jj" -i .$ ( .-Its-*W : 11* 13 0 A:A1 304 S f&1 ,
~S. AI- I@0 %a &a aI 4~ 0. mo g 0#. I
122
SUDJECT: SUBU0UTINE COIPUE
PURPSEZ: SUBROTINE C0IPUTE controls the calculationof the installed performance for a singleinput case.
METHOD: Using the input performance data COMPUTE firstcalculates atmospheric data and the referencerecovery factor (NIL STD 5008 B). Gross thrustis computed for the input WF, W.1 and P8/PO.The inlet module is called to find inlet dragand recovery factor. Then a second gross thrustcalculation is made using values corrected bythe recovery ratio. The input array to theafterbody module is loaded and the modulecalled to compute afterbody drags. Referenceafterbody drag is obtained by interpolation.Now installed thrust is calculated by combiningthe appropriate terms and the total calculationis complete.
USAGE: CALL COMPUTE
All inputs are in labeled COMMON blocks.
Input variables are:
Mach, ALT, PS, P8 /Po, A9 , A8, FN, WFT
SFC, WO , Table 2.1, WBLD - f(Mach, ALT),C
and Table 2.2, CD = f(tach).ABRE
All of these input variables are direct inputto the program or immediate consequences ofthe input, e.g.
SFC - WF/FN.
SUBPROGRAMS: ATHOS DRAGAB INLDRAG
PERF SQRT TABUl
TABU2
13
T" f EIt)
wa ~ * 1.0 1.
WRFI~ 1- UF 1 .75Iah-1).
mm . .. . sm m
.- 2
fm - mm mb/m m J
B E ab +2Mc2&minm mm;; mm m. Mah2
V2 a (t) M URF)A
oL7Figue2 LOWCART OR SBROTN OPT
offli14
W" - f Oa. Aft)
ff -- W PvThnL IN* RG
r mmOR
FO OUPT ADDITIONA
A.ON.T P1 A fEWtW. Au'G./t. un
fw I* L4
F~~m2.' F TOWHRT FOR SUTPOUT.ATINCOMPTE(CLt
f Rf% .1,r?*RP. ,
(CALL PERFI
F% FF a F m"
LOAD WJ
7C%.r.~ Ch 2S.2CDI A
'IRI
* PAUPREF - CD, AMX0-qi
I WW I S N - D@I ý 111 IN AIE
L...m PC WF1
SFc - WPT
FNc
Figuire 2: FLOW CHART FOR SUBROUTINE COMPUTE (Concluderd)
16
W4
IL :
u ou 0 "J ) u
I-
M 49 -4
0 Z,
0a 14 1* 1$-
#a 1. 49 101 Iza
19L U fAS I&I
J J00'3t4-'Z3 f," .0 jJZ a0 IL0N a4 a.
41.1 ,2 fl 0XC'72 14 4 n Ih"1. .
0 "Z
%4b b. I. Ao fj% ill. f 6b Ut I -N - - -z
;T d00Za.4. o 4~ we .4 '. *.7-92zz -
.21 a11 7 I. j 10 T1 *I lv .2 A K 'IT -1 * 60* lb IIte IA It N: 6- b64 "i Iaa-a1* 11 n % M~ lM11T04 6.A.42 A. I - ZL f1 A140- til 0I4f w. V. 0 *41 4- LI 1 1 6 . 44.
'2 1, ?~ 'n I. mf. w I' zzrLE. .. 34 j1v.sl 191 0J. ' U14k 4 -
CA ~ ~ ~ % f LU3 b60".3ve o 32 jv- PoI 3 v 4, ULre -%j. wIl aI. 'A. 'I u 14fl v
ni'm * I ~ - * ~ *
5 1 no13 NC1
VbI ma. e* N C44 *.Ni N .? no C4N ytw YtNtUNI %- 41
1V % 1%fl,4 r .01 m m if % .4. y N "t 45A. III~ PAV 0 s LI. 31 .4I 1N1
cac I 1 1 2t2 41az~:1 :~ (1,J 1-0 Is j; i j %a A.p 11 v1l.. j
C.ieK 0 .K 61 K1 I La a ho 44 IL LA I r 9 S044U 1 '11 LIP4
17
C', is CA nIX
0 10 I
.W.
04 x
06 1.4 9
( C3 i z
W: w 13-I- ce wI
I00 b. IL
.4 4 91
0 II
0. C301
de 2- 13! .4-99i
do 49 0.2 A t11iaL I. rzL
'0 41 IA ae v-L %JA 4ZWU
UF IL IL 1.
2 4 of 3 1 5 .3av ;I-- - 61 1 iCL W 1.16 0L A 9 4 L . L o f t f I o 0 . f 1 s s f i t 1 o I f I f .Z s s i
If ^3 -. 4f~' -4 'A'O4x-4I 8 3lo l 0 C .t. 4 1. rYE Ina N 30'r, 4 .4I U ~ uI yI W J..~~ .4.4. N -4 \ r VAjN j0vm6 1-. 4, 0 .2j0
g I II~0 ILL.I0.w 4 1 4 0. 49 i.9.. 9.1 4g tS H9 .9 H2 -S M I 44 9 g A H .1 Q rH (3 H '3 -1 H3 #L0 0 (A U. 2 HIt A
Q IIL
A -a ks .4 a In %Q N .4 N * U% N IN .4ltuNa 0o n u J4 hD .4 111,pI.6A N*T 9 .1% 'uA -mu 0% ON. N. . N.' -1 .IN .4 .4.4.4 N 1j "1 ".4. 4. 4 4 .,d- 1 4:. ý4 .4. Il ."jiN r J:N 'i ~ jN V vJy
13 11 '112IIJ r3 12 -3 n LI
13
I IIli
I I
a I I '
!• I
I I
U•
a .I
J.I.
ID 0 I w U Q
C, C2 I2C.
em ma a N c X c~~.4
P N. IN. c WO Woo 4 .4 -1 P) I- a3
O I MI I M ý ) W
Q0 * Q L)(, 0t U 0,L .If N .4.6N2mp N . IF a~ 4.j .4. t C
a1s M 4 , INN- el -4 0. WO 4 C,02P .l 4ý ýpCN 44(JP(N0 C In M43 v nOnC N13CI ~ ~ ~ ~ C C-3 a6 Cl,~i~Z'ew~~.
CD cl IW7 " ~ M C3t 13m1 vr 313m 1
N40.14 4 3 j00
C~UOU 0. .) UU U C.*~~~ C N 'm In' on@NNNND N f MN N.41
.4 IN.I* LA 3 13 mC )2S .3 L* #2 CO's. 0sP"# 3#2.)on:
N2q 2C a L L3, aJ~' .e#i.5.J2,t3I~xý jC ) .J 3im 2 .)t 13,sN~~1 3 It0 1.a0a in '.4 .7 aj a#, 3 3 ~c
V) (A C2 3)g, P j C C. C .2 2 #1 ca vs 0 C2. I Cll3
2 ~ Co zi o wow ..3,tJ U U 12 U( -9-490 0"iO NE, 0 V I0W 0 cu 0~a b. i".3 rf 2 ) fl4 Oa ) a m t0P .~ 4. Y - I.9-
0-~. 2 . 11 .- 0 n 0-.s2 on3 Z N 4, .4.,.4 1 a~ N.r43f¶-4 I 4.1 w
Ito L5 I, . 0 (fll u f33j I UL, i ( .3 t.I# .) J L)' 1 -1 b0 6-j I.. z z a 4 ~ ~ Ua m 1 CfIit fti a a I '7A' " L 3 r 4 tl a4 A faI
w 0- onI s. .1 4 DCS J 1 ' ,
013 (A1 2 tjW m- (A. .J1s (Aj C3 U 0- jrlU 1cp 2 dl ( (A#A m .b , a%2 a s .2 , lc , l Y. 13 C C s12'/ V-r IVC1N
ta. I L.:~ .) a 4in 6. Q7 I '~.' ¶V.li z- C1 , I - '%I~ .sIT . N r-30 W140 m wZ : 7 a' 5
--l*l- In
Ni wrV 49t w 444 (j(a w01 v!( . 9 V 2Aý 2I
''2-
SUBJECT: SUBROUTINE TABIN
PURPOSE: SUBR0UTIN.- TABIN reads the Inlet performancedata deck, Cards 3.1 to 3.2.12.
METHOD: The input deck is read. Table 2A is enrichedas required to evaluate that table. If inletcapture area is not input it is computed.
USAGE: CALL TABIN
All COMMON blocks in this routine are filledby calling this subprogram.
SUBROUTINESCALLED: SIZINL TABLI TABL2
TABL22 TABUl
21
S21 V
I b
Iot It,.
49 Iz I0 - 13xc xiN W~ I- CO0a z 121-
0 4 z I Z 1-bI1-z4 ~
10- wuv
': :-" 1-'I ID O l~0 !0 Il II~ z -cc~ tt A
I !C .9 1aN I Xt;( l I-I zIN Al
9-C ~ N Z Z Q T T(A 11W4 n9 1W . 4. 1 o II I , 2 I tboli
4 b II." I N(YN 4 M t 1.2 TxfI I 41-2m . DT 'ltt o l DxzN1-- - -
.. NJN1 f ,04f o A0- '. :21;NCOb-t fm
VS-4- Vu .N4-w-
11 1` 11 ..4N* *2.2"..N-%2 *, , iA V 'I le 45, Z Z-~ ZN~'~~J4"N Z . (fLJ Z- ZA. Z 04u X '4. 4.
mowo 0 K440 m 00,0000 0m no 4p me .'Y 4 me- 4noIT -. 13 4 N ItNM - 1 4% iu ý CY - It..b-Ell .3 0. 3U UQ 36 . %L 2. (3 .0' 3 P0.4,1 J Ni
z S*4 Z % % tl%-.*( J W*J ~ aa~O Z
.4 4-- C3 r4l. 1 -. 1~ af i .4 j 'j-3 I 1 - 4 -4 -- 1. tl4% 12% % % ~ % %I ~ % 4.~b es4~ 4j 4 Is.'~~ .314. C2 1J4 M!4 -. 1 2C
w i 00 l C2n .0 000042 0lC 0. 0J,. 0. %nO C30 i 46 a 1.3 a 0 ý 4 0 C2.J 4j4L %a C31 .. ýj 1. La4 j j Cl Q . 3
CA'
Y 22
I fW.zSAII
I' I
( .4 Z ty N C I
-4 -4to0 ;'4
ejv, 49L
e t0 I$04 9 1 4
to, - 2 1.- -W 0- -1-INb. b
Z. %4 (6A r3* .4 JW4j . .4 .4 j j 946 4
W .r IL 4041. n-0 Ii. IL It) a11- a0 af T r .49zM eatY b4 -j1 - 10o-0 J I b J"l .-. j.b- J njb -yI.J"*z% f~ "ill4 fill "- 114. 11 " 1- t- fW
i a UT UT T t - I- 553 4 IXVX' 3U A. &2V( 9e1 t( L) .4 .4 '3 (j 07 7I.3 Z3 a4 .
'4.4N.00 f N.af .I-) V18 'IIN U WN N 'IN" j tjC4#. P) 0 "YW ..pi%0.J'0 ONg r44 ." .1j I 'N %D tn % N N i %00O - 1mC-" 1.4.~ weU '1N4A 4 4 4~ 4 4 4 t .
Fa&"'ic 0A2 N IA4f A t.31 .11 %.3 aUf' 4 .1.U6 . Stl o'. j .4 .4 4 .14" I .4 IC2 cs w, C3 u~ C- 3t . 44'wwC, v'3%3: 0 4. 20C ' 3k . jwwc~r wC31I, -z -11ZW . W 4 S iI J dt I ? 1 a ,J J I. 4 4 ? '0 ?I t' g ? i t I ! T J2 3. ¶
Z N,
N -4
' I j
ujz
a n
ar- f%.U%
Il2
.- B~
ZN
SJ b"4 p
14 ~ a.4t PP.4 N
QI 0 C4 1I&% sc % if2% ;
04 (A NN4
C-44 IN I g z
~~4C1.N4i O.4
flaU u~c3 0 U uUV C3 Uu
IIw4 414 e a NNN41 4. "J 0ar
x x 10 N a co M M
0 N t*NDaU"Co. 40 I .4I MA -4 ll 4 IU-4 .4N
'? A In . 1t4)ee " mM a .*Wri " 1-4N Y 343)NNNNN UUUUI'
Ii ~~~ oi IE~ I~ ~-I I-- I $A
on4 lc ."!Z. "'ll2t-4 IN, ) 25 no "A'
-- ,P ) '
us9 449! ..4,- 1r 21 4 4N 3 A N
oools# 13 M IN .2 N N"In a
SIn.. .4th N'g N**M 4r~ 1M 6
* 1 3, %3 9. 3 SS LA b-I3 'I 4) cA (L~'A .W.a at o I 1- 2%- AC j% JI -1ý ~EJ fA J,3763 - 'J t z'. x.)e
atC c l 441 P t a a 4A42evf a I -3- 01 2a5 3. -- - -
SUBJECT: SUBROUTINE INLDRAG Controls the Calculation ofInlet Performance.
METHOD: After initialization M is interpolated and0
compared with the minimum Mach number forwhich inlet drag will be computed and withthe start Mach number to determine whir, inletmode to use. Low speed mode is computed inINLDRAG: Subroutine AIRBYP computes external-compression mode performance, and subroutineAIRSPL computes mixed-compression mode. Inthe two latter cases inlet drag coefficientsare interpolated and inlet drag determined.The outlet array is loaded and subroutine iscomplete.
USAGE: CALL INLDRAG (XM, P, WE, WS, DINLET, RF)
XM - Free-stream Mach number
P - Total free-stream pressure LB/FT2
WE - Engine corrected airflow, primaryLB/Sec
WS - Engine corrected airflow, secondaryLB/Sec
Output DINLET - Inlet Drag LB
Output RF - Inlet recovery factor
Input from COMMON
XMMIN - Minimum Mach for inlet drag caiculation
AC - Capture area - ft 2
Inlet Tables 1, 2B, 3, 4 and 5
Output in COMMON
0UTINL (10)
SUBROUTINES CALLED: AIRBYP AIRSPL AREAF
TABUl TABU2
26
Machoi mf Mach from Tae I
Mach: Machmin AREA= AREAF (Macho)
C D sp1 0 .Q0 M do s A
COULD 0 0.0
Ao1/Ac - 0.0 CDSPL - f (Aol/Ac, Macho) from Table 3AolAc -0.0
CAo/A 0.0 C BLD mf (AOBIAc. Macho) from Table 4
RIF-f (Msch 0 ) CDeyp f lAoeyp Macho) from Table 5
-- CDNL , CDSPL+CD 8 1 0 +CDeypIll
00 +fpto Mach 0 2 (1+ 1j Macho02) y-
L DINI. - OACCDINL
OUTINL( 1) CDSPL OUTINU() Aoa/Ac
OUTINL(2) a CDBL OUTINL(S) UCOINL
OUTINL(3 = Co 8BY OUTINLI71 Ao/Ac
OUTINL(4) - Ao1IAc
Figure 3. FLOW CHART FOR SUBROUTINE /NLDRAG
27
CLw
r 1A
.I.
2 43
ev b.a6
1A
40 I
IN ICZ a-a-44
I~4 i .. 44 a. II: N 14 *4 'A
04 At .4 t -I4 ICT us
*~~~4 x1 j4 ,f
0, 0
le z m I- -a -a*1 w 32 223 2c t0 Is r w4 I. Jr W 1 4 .1.60I 40 -9 - - -I -1 -h - -JJJJ. tz- 04 AK F,4 1 N I 9
.4 E KZ EZtZZ rKzi XKKUz 3u O.bJ Hd -Ifj. in. aeL-Ea, Hu 4 .1- v~ j~ 4.4-4. j j
Im 2 .5m c z CIX l ( 1 1 . 4 AJ U Iof 0 _ _ I
.4 N
4.46.44. .. .41w .444 -44.4.44.4 .4 4%1 '"t%~ ft% 4)"YA w,. V F- ' -104 t -094 A44
I~~I -ftIA
28
$ q q I
I II I II I
'*1 II I I II I
( I* *1
I jI I
I I
I' S
I *
� I
* I
I II I I
21
=C 4 ca1!~C 1*'f
, !II I f I I
:1 41 44 t .
.4 .4 f* oj
%2 .4ra ~ ~ r9 4 yf s 4 - Ns
f3C 4cm mnN*E2* mlvr IA2 (A c,43 co a k3 13 rz..2CC .1
z Omm 1b.OUS
N I **e so S
4y z z 1 0. o b. I-0
.41C. .i UU'UA .4. 4 a, -,3..4U CDC 1440-'qN 4
f 1 @13 k" t f2.% 63; oD1 2.4cIs ..L3,ty 0 V) cp M 0,0 ca "O ~ J ~
fe w A r. .4.4.4 7b
zasa
!II~ 4 . .4 .4 'S CA 1.. 1
'* lam9j .4 tN .4.4 .. * O3*~11 12 N ca 002).44'~11.3
2@ 1j C3 J N 9 -a!.~'3 2
L 4 46 6 I 4 W 0 ' 1 4 S C r
U z 1 1S *1 14.4 14 4 ~ .1. 1 1 jf #o l
ZI c .4 j -os -. V94 I-* 120 6- T 2 1.2f'.e.~. it" '" T
ald M 3*4 CAJ L) L). A. Z S 0 v Q .4J'~ Or'. .3.,) le .4 u1
Ow X 2011 -1 IA t U I%# I, I ;- 'iiAn
(A0."4--1 $. 'js-8-0j es %S X h6 A 4 i i
SUBJECT: SUBROUTINE SIZINL
PIURPOSE: SUBROUTINE SIZINL computes inlet capture area.
USAGE: CALL SIZINL
Inputs in C0MM0N/IDESIGN/ design Mach andairflow.
Tables 1, 2B and 2C.
Output: AC ft 2
SUBJECT: FUNCTION AREAF
S.013858 ( I + L_; ! Mach 2 2 (y TPURP0SE: AREAF = Mc
Mach v -
USAGE: A = AREAF (XMACH)
XMACH local Mach number
31
3
gSUBROIUTIEg
"SIZINI I
MaChODES - f (MachoEs) from Table 1
Pt2 /Pto - f (MaChDEs) from Table 2B
Ao/Ac - f (MaChDES) from Table 2C(:
Ao AREAF (MacoDES) Wc Pt2,/o
----Ac - Ao/(Ao/Ac)
RETURN
FUNCTION
START I AREAF
L ... l
AREAF 0 ,013858(1+ Mach2 ) 2(7-1)
Mach VT
IRETURN
Figure 4: FLOW CHART FOR SUBROUTINE SIZINL AND FUNCTION AREAF
32
ILI
Z, IL
$-I-Q I.)4I.. Z!Z 9 N
.4QD AD
(3:0 1 4 4~
(J - 4 i ej .
noJ IS W.m g -114 *.4
Z ZZ 1 U W o- Z4
W%' 6&' ~ ur
Iu*0c)CAW.,.. 33
C-0 C,#4 'a a'
N w
Ai
.0 .1CI
( 'L to.)
j. ej I.A *LM c c a,3~
~x 0
a ~00-430
N Z ý I 3I.t
z 01 tUUut0L% I- 0 N3 -4,41 4.s1`*,C 43 2 -a , 0343Cf, I
N j . rý q.3 a 9I . . 1 t
* A0LJ 2LI L3C (AI,. 3 . 7w
(A .4 1- 1 M P
'43 A W Z4a1 IA , J '3A.
f. I' til 1- 16f C 1. to It- 0t ,1.
IVt ty, fm Mi' Ij 0~ lI 6- 0 -.1 4cC5 I11 It -9 P. P. -: I I1, ~4. 'A .4 l.I- l x e'Zj J
34I0 ,
SUBJECT: SUBROUTINE AIRBYP
PURPOSE: SUBROUTINE AIRBYP Computes recovery and massflow ratios for external compression mode inlets.
METHOD: AIRBYP matches the recovery and mass flow fromTable 2A to that obtained from function DEMAND.Table 2A was enriched to 41 points per arraywhen input by SUBROUTINE TABIN. AIRBYP firstinterpolates in this table to develop a curveof RF = f (Ao/AC) at the input Mach number.
The 41st point of this table represents the
choked flow point, in Maximum (Ao/Ac). DEMAND
is called to compute (Ao/AC) for the RF at thechoked point. This Ao/A(C is compard to th,. A /A
of the choked point. If the A0 /AC from DEMANDis greater than the maximum Ao/AC then the inlet
is choked and RF must be found such thatDEMAND(RF) = Ao/ACMAX. A Newton-Raphson iteration
is used to solve this case. Otherwise the inletis not choked and a solution for A /A existsless than the maximum. A Regula F2lsi iterationis used to match the recovery and mass flow.
In either case buzz and distortion limits arechecked and the other mass flow ratios computed.
USAGE: CALL AIRBYP
Inputs in COMMON include Mach number, air flow,capture area and inlet tables. Other COMMONblocks are- output.
SUBPROGRAMS: DEMAND FACINT IFIND
TABUl TABU2 WARNING
f 35
:START:tD
BUILD RF - f (.Aa/Ac)CURVE FOR INPUT MACH NUMBER. LINEAR
INTERPOLATION ON MACH IS APPEIED POINT BY POINT TOUTHEENRICHED TABLE 2A. THE 41ST POINT REPRESENTS THECHOKED CONDITION.
A(K)- nMA Tn(.11-AA K I))AA(.I
No Old CurveNowIs
MWI Lh StilN Good
MMw(hom - Mach 'h
INTERPOLATE FOR MACH IN ENRICHED TABLE 2A THUSLY:FOR K a 1.41
INTERPOLATE FOR MACH IN ENRICHED TABLE 2A THUSLYFOR K- 1,D41 P(K) XMFAC (PTAB K I + 1) - PTAB K(0) + PTAB 1K, 1)
AMK XMFAC (ATAB (K, I + 1 ) - ATAS (K, 1)) + ATA (K, 1)
WHERE I IS LaWER SO)UND OF MACH INTERNAL AND XMFAC =Mach - Mach()
Mmch(I + 1) - Mach (1)[IFIND owl FACINT]
, I
CHECK FOR CHOKED FLOW CO)NDITION
C -A (41)L m - m -" m uI I FUNCTION DEMAND COMPUTES|
A2 -DEMAND (P (41)) 1 Ao/Ac - f (RF) I
FC -C-A2 L-___. ________"I.. ..
C <A 2 "CHOKED
C:A 2 FLOW"
C > A2 C
Figure 5& FLOW CHART FOR SUBROUTINE AIRBYP
36-!.~ .-
Cuv
0 ý REGLILA FALSIRF ITERATION
-7 2A TO FIND_ 141141) INTERSECTIONJ
NON-CHOKED FLOWAo/Ac C
L R I fA/A)frmCuv
=(RF)
,F c 4e
1:26I > 25
I EP
l< 25
L Ao/Ac -10C F - IAolAc) FC
F - FC
Figure&5 FLOW CHARTS FOR SUBROUTINE AIRRYP tCont)
CurveNEWTON-RAPHSONcA. ITERATION TO FIND
RF P~o)INTERSECTIONRF
.CHOKED FLOW
A
AolAc C
Ao/Ac - A (411
F - FC
SECOND STARTING POINTRF , P141)X2 RF/2
F2- Ao/Ac - DEMAND (RF)
I -0
Xn- RF- F (RF- X2)
X2 - RF
F2 - F
RF - Xn
F AoAc - DEMAND (RF)
IF 1:e iI< q 25 > 2F A . o
! g, ro .' FLOW CHANT f 0/? .5UB/ROUTINE AIRBYP (Cont)
"ITE RATION r Lat dasFAILS"or Ao/Ac:n &W
is Miimumfor BZZ *f (Masto rtion
Liit
Mi*nu MachA.aho rm~be
is Miiu fo BuAc/ac f Mach 0) fro Tabe n
A1 *Ao/Ac .BZ A/A EO
DISTOR~~ - f .- ,..) ro
3PJ
zl.
lq4!. :: ;: I
ICI D
C ) . wI C .4 . ,
04~~*~ la: -NI mp . ' aI- s U
IL4 40 '1 . 4 .T , z1- 6
-. do 4
- N ~ 1 0 It of 1 2Z 0
I.)4
I .,.r Ne4z3! 0
toN 48094t
010 N3 00 1
*s i' m@' . f, .4. 4 No N N A'ISf.pt-f f
C2 -. C
:- & i ). ~ g C2 1.94
43 3 ;IL 76 2 JIAC:30Cj:33 I aý L j, a is Ic s 6" 3%
lo
'I N I
L D- of I.,
94 0
I* a. I'*' I. r s4 -1 N(
I . U4 0 I4
I , ato a XX
Al 2 a 'I E3*
# A 0it h.4 41 z I-- 0. 1 q oc
-L k 0f of-- Lba N - I.- 4 *, %0 -11 N A., C 'A - Aj t
IL dfl) N ric (otyad;CY J * 3 4 5 1 1 1 0Z41t. CYX1- 0 ll I- Ia. 1-4 X . 6 r j o" QI .- 4 N
am 11- N ,. I13 0y I204 -- Xý4 4*,u &1 1. 'g,0. 3. - 1 ,. ,N
Il. 10 zA Is 11 r. Li, O 0 4 oe 40 49A A- 0* II.C1611, ; 7 0,S NC f, IT4.- III S-i. -7 el3 d.LN;ag W
to 11 w r, s . C- 0 If 7S %L N~ a JJ -q9 1
I,- af j CLL ~ OJ I..369 1 j . c 's I-- a.b- 4 6.C ~ j' I.- bJ- - . 41 -
N Ut lb N j404o 1 , f0wo N 4 0 IN J S-it.4 ft N .J * N,- j vIj y j to wN'4. U " voN6 t %zN-0-0 G N4 ww0M0 0. 4M N0. 11- N w 5 K1 y O" n ",J " I J
j 0"4,0 41490 zwL N *4* 4w loI.L- 061 a 4UX 24" 9.
0 i .4 ISO~,O 0 - 04 4
.- 4
z3 N *t) N 4 " 4 N n1~J 4S 4 M4 jillN N NN.:,p f3 * tn ifulf 4 .4 - t I n 1 -M %1.' " "i
.4 -4.4 .4 .4 .4i.4'4a( Z.4 49 4 40. . 4 0. 4 I'9. 4.4NN N f '"~. N 1`4 '30 ~N 'V. 2i. .3-Y *0 , V... Yb
C, ' , S ,3' 'a U4 0, N 'a 3 c
Oh C33 0a It 0,13 JIi 0 300 Q~0i %.3 '0 C J ca 0 1. %2 % 3 w0 w6a .3 jk .: . a %3 'C j o % )41
a lk N' )Af om. 4aNN sQN0.C
Pol w I %9 C . %226. el- fI se
VIll
46 1. 1 049.2 .4 W"* P5I
mWk ski ' 14 .44p. . O) r P4
45 to. mo0.
*~~~N .4 fm 4 'li
.0 .4 ffi f rm2 $AI .4 fl % O. o 4- 414 fyN NN*
.dA VA tsf on el f - of.4NP nlm .4 " Ntou.4in1 @41;f 001 30 6 10 10 U.3ra a3C
esta 00 * 0 10 " C,3V
es "142 es1 Laisra 44 e4 , 4 Go . 4 43
.2.4 . 00#34.z"0 .NI
es4 aO 13.4 oolr4'j s phnngt
lotw IW w ;*%
Ufl ~ .4 y
00.0 ~ .0 4*--S 444.2 42U. -4-.4a4S fl Q. . tf0
CA .3 *'CI .4i A- 'sAL
1.2. -JIe U) . 4a O V %2" to 4ai41 .4.4Ad.4 , N ' .4* 1 O9 1) -1 1j- 1 * I
or'0 N N -. 6.13eb 'aN ft N s .6 10. 0 .4 , .A N I '93 'a~ Ga " kd SW .-f .4-441 'u
to m1 01 IN. I. ~ow .s IL 44 .4 13 2 11 IL . 2 I.-8 o-) 4 So
V~~. .tj.4~ -4 -4 CM0Wpal~9g 4 *i * 3 (A b
L2 *I,1,0 814 91. . .S .8 A P 4U ib2.3A-4 - tf@ .A) " % ..
es.: 41 V sm-e A # M sU IIf 4m o'3v 6- a lIA lla t 0 4161 og a A ' 0 04-C3 3-I1 $ -A
SUBJECT: SUBROUTINE AIRSPL
PURPOSE: SUBROUTINE AIRSPL computes recovery and massflow ratios for mixed-compression mode inlets.
METHOD: The various mass flow ratios are computed fromthe input airflow and by interpolation inTables 6B and 2C. Recovery comes from Table 2B.If bypass mass flow is negative; recovery isrecomputed so that the bypass mass flow is zero.A message stating that the inlet is undersizedresults.
USAGE: CALL AIRSP•,
Inputs in CONNU include Mach number, air flow,capture area, and inlet tables. Other COMMONblocks are output.
SUBPROGRAMS: TABUl WARNING
43
!3
SART
'1. f t Mach) ftom Table 69
Ao, fMach) fromTable2C
Ao Ao/Ac + Aog/Ac:
jAc____
R - f (Macho) from Table 29
4I ....... I - iI
j.AraW, RFAe Ac
------ Ao/Ac -AoE/ Ac
E At
~AOSy .m
"InAc -Is AAc RF -Ao/Ac = -
Area Wc
' ~RETURN--
Figure 6: FLOW CHART FOR SUBROUTINE AIRSPL
44
-0
* .4 L4 I'
-0.
we4
ha fu.a .
~I Xz ii 00.;
wI O'.2IIII!~ ~i~ 1 0 0-i + itLO0U
0ww I. i~X -(D X M 4 m u
J542gg OA1 2
64-14, ~ 1, :
CL-r 1.1 (11 to is .*P.*APclCN .N 'II
a. I- 0 f 1. J' w0 0qg. 1-1 .(4 CL 9 1 I 4 w . JJ C 0 1U
% -lz0 C, ~w~mt
C1 a IC4 0I -4 I445 In l 3 a
111 c" IC
to N .4 0 to W
:.4011.4.40
~ !whu C'tUOLI
Ica CA0 4.4
r
v" H 0 4 146 U% a0U44 .. 1
*ý ca .4U .4IAU ,4 0,C. 1" 0 4 I0 YND tj C3 N -. 4 14.4
0 y C3o . 00 'a rv. 3 0 .2 0.~ a~0 a 'k c L3 3 33 CM 130 12
' 2 .8 LS C3 t .a - 13.1sC3 1 3. 33
'- C a 4!I ID caca a 4
YIN 3 - 4b- 44In -1"' 4 40
IA I-I jA Iz .4W , Z-* *r, N A 4 t .4
* La M, c 14 J
t3,. 0'. L4 J13 (Y Z 3 13sJ'JJ.)J 0 3. 0- 4z Li 0 - C-I m es -Iii.2 ar 3 " 0I'sI~J I ~
1 4 Ica Imo a .3 ,30 40 CJ 'I Q j"5 alf C2.3
j IIA
46
I
SUBJECT: SUBROUTINE DRG
PURPOSE: SUBROUTINE DRG computes bottail drag forconvergent-divergent nozzle.
* METHOD: The built in nozzle data tables are defined inthe DATA statements of this routine. Boattailangle is computed; then Mach is interrogated.If Mach is less than .9 the subsonic procedure,SUBBT, is used. Similarly if Mach is greaterthan or equal to 1.0 the supersonic procedureis used. If Mach is in the range from .9to 1.0, then the subsonic procedure is usedwith Mach equal to .9 and the supersonicprocedure with Mach equal to 1.0. Final resultsare obtained by interpolating between the twosets of results using Mach as the independentvariable. This provides a smooth transitionbetween the two Mach regimes.
USAGE: CALL SUBROUTINE (DMDG, DBDJ, LDJ, EMF, EMJD,PTPF, THETA, GAM, ICON)
DMDJ Ratio of maximum to jet diameter
DBDJ Ratio of base to jet diameter
LDJ Ratio of length to jet diameter
EMF Freestream Mach number
EMJD Jet design Mach number
PTPF Ratio of Jet total to free-streamstatic pressure
THETA Boattail trailing edge angle - degrees
GAM Ratio of specific heats
ICON = 0 circular are boattail
= 1 conical bogttail
Output in C0MM0N/A/
SUBPROGRAMS: ATAN SUBBT SUPBT
47
Define Built-in ow
Tan~
2(IL/D)Pr - Tan- 1 (Tan (8)
d - 57.36
MachMa 1 Compute CoT CDBm and CT
: 0.07 Using Supsi on1c: Method
COIIIP~~~tSCDBTT COB. gnd Coo sn h usn c O[C(CALL SUSBTT.<Mnh < 1.
ComputCDB-Tr CDB. l, &W CDTotl Usng the Subsonic
method with Mach Number Equal to .0
CompuvCOBT2, CDB.e2' and CD Tot2 Using the Supersonic
~[CALL SUPTIIT
CDST - COST1 + ST-|C~a - CDST)1
1.0 - .90
1.0- .9CDB ,CDBM + Wiph-.)JICDTM CDs&,
P-D~t - D~o, + ich-.9)ICDot2 -CTo. 1 )
Figure 7. FLOW CHART FOR SUBROUTINE ORG
48" 4
48
et 4 Al
I I. I,
04 4 ItII I. o t l 41
EyI 0
.4 .9 a ~cm aUN C S)a n UN 0 U% LI a0
;I.. 1; z% 1 C) "s
All -)- 914 SAI IN CefC32!2MS
o .a p .a..... ..
V W, V. U% %. I* Ps 10 3L
ah L6-U Z Z 9 inD4@ av LNý 4N4I
PL 94S-i CI- C3n a fi -2 4- m. maa ~a
a* ft-O4. C.3 aS. . ....C-2.0E14 Il1% CV. o 1 I j3L 'SQ JI1. . 2 4j ON.
.. 3 4 .* S30~.. 1.- a Ma it aD a IS a a.LC L& 1 ý* NC
1 044..4 1 aa
ID -
S*f* oi ,~ dofI o 41 b Id NIl !h a .a n Ic 1wl N--eg I-9 14 495~9 as a9: aaaaaaaa-
15- IWai4 .1 0.. 10- 49 *9 4 Ix)"1. *ftI-.10 m a c ~ .a,9 It -2 .4. =1 a. $- b- b.. .394Nb- 0
% . 1 0. 0 ~ b-S aaw a. av C1 ,-a 491- .9-4-
*4 44 W4 I. .4 T4W4949. 4. 4 a4 a4 .IA ~ 4 4Lan~ 'a L.a '
*2( 13 93 s'fl 0b' ar a3 fIIA, A a . "% ..3 ".) ~ 1 3'.4
Il 'I Q w9.< h '- 99.99 l -0 L a- a a aa aa s4a 3apa
C, Co toOy# 4 i .-
II
I
I I
I I I
1~ I I
I I'
a ta
"" Ia I I 2 a a
* 01 Ja*0¢1l • .t
tr N
4 • i I~o @0lii•* -t.,
(,! i . 'ihli I, ,
I • I ~ • l%¢ • t I • i*,~ *I lI
*a94 m 400U nC0944. 1A. - (0
t. 0
CPIT IN IN IN . . .. 1I 1 " . ; I
To
N.9 - 1. I 4 ; a 1a%4I0
4 . U,% N . l% - 0i l il
A . :
P. *%'4. W30 -4 .4 4ýf 2,3 1. . ul. La F
C0D 0 0 L II g,. -0 (
it 6. 4 _ A0 . 0 040I c Dp
^1p O II
9 04 a1- ~a
... . i
ra a lt~ I 1; e M C2 13C -CsV A 3t
to -- a l M . -a r JA x .
f; D 0 0 * (Y. 0. % . * I * C; I4 6""5 . a. . * ' i.113a e.ll62 1. •* - J .0 i 1 0* r
•a :' * i. aa Z* *l0 4 ' 43*'
0 9' 4 *e 4 0 ON t o w t*g'' ( at41% K *
t; QJ 12c.In Is ' I Ig MI 1,,1 C7 Is I'D. N.N. ý41 All If$lI
94 I ^4 C3g 13 al944N * *4 n n In tac0J~,,9 if 'D4 -
0 4~ .1 fiA ..4 (Y4 a.. gj4W )..
.0 tA I I I "% C 01 a I
:In
N 9 0 L 'it.1 'es-i .44 . 4 0 % '9.9.9.9.. 0I .4- 90 09 4 4
0s b.ico ,S4 I.- a %-I-wZ1-0-6
A 14~n 499 .111 9
.4 4L -4 4.4 .44 444 4 .4.4 .44 .4 4-4
a I toj jr '-vZ, 0 U '1 %3 U: 1cmmc
3-2 .4)'r ri 45 '43 .31,' q'.4 C, ~C4030 Aj 4. I0 L1 "3 3
50
I I
CNIi
IWOI
a. . La 4,
* 0 0 aN
C, 1 01 . I
to, .. t a a
@Ip..
C; k. IA)ovo PIPI Is~ ca es"" 14'N 'NAa Con
N~~ .9U1a
C's'I MII.,' %2 5I 14 U.0 ca (a a It . 3 .4 am tI ILI: w U.1
If % & ) is CIt!4
." *.0
ty I N 41
N~ ~ N to CcO ;N 'f~ICa iN -4 .i Ul kI A b-'
,C 4 yf PlO on F35 ec, In ItI W.AM,'Dnfnr Ox11 M,1 "I".13.1 -
s 25 - ~ 5I P. -40 If W U. c it : 111 1 IM A HI if 0 r, J J -4 Z 'A
0-444 95.-444 61 911 T l 4 151 11 'jjJ 'I50 j5 0.4-A55., ot 6. 1- If5 5A J .-% -6-n
.44- 1414 .4 4 1 Id ILI.
(44
III - .4 4 4t 4 l.. y 4 ol SANo imia .4 j N3 U -
.4.4 94a.4 .4 -4 -4.4 .4..41.4 OY ly .41.4 ".4.4.NIS'ULI ~~~~3 (4 23 ',a ,20313 3(S 939j3s. 3I
I~ I 6 3 " , ' 'LsI t 1c 1 xV 11 3 ,, , 3 31%2 3 4239..aC1V C 's t ,91;11S%1.k
t g
I O
I a
( "
I I
I i I
a , III
SI i! .04' .,
S4 , I
*$ I
a . 1 1 110 a I*10 C1L" j'
to OW ICAq aP NtNNIIU nC, 94 94 to4Pi I D
in Ij Is Pa 4 0= ae ,L . a4 2c
I I o l I fII I 1/0.4 94 N I
it N N N (Id N NE %N CNNW~NNN' NN~AI.
64 C, ' ma a 0 cz 40 0 urs .2 '4 C3 .
a els Cs C2e C*cpC C C
066 2 2 2 z1�4 0.6- .A I-.B
944 N.NNN NNNNftNNNN Iral!0cwu r~a omesu33,2f3..a
10 IN4N N C3 m 43N 04 .0 Om 4A a .0 I 0 oN
I a4 I*j CI O, 42 a I L 1 . "
Ia " 2 j'
a FA , a aa ! 43 f3 oao a.=aC2L4aaaCID, (.
-3 III 1-4 4 CID4
U~ ~ E(A tIo.9Pu .4 J fl94ETIfl~tN ~
3z 2ý C S3- 3 C IS 2 La A- 'A( I AI a It f1C 0 U u C.3 C.) t I ( I L) f % U 0 b.- 1 6- NO
:b. x 13 1 4 6,4T' 4 .4 flI - " *.4 n0 -N4 F 'M .4- It C2 de4-
w .4 (A%3 n'C 4 I 1.3 301j"a '
(A 14 r- UWzI I IId I I I~5 I L".
:0 t 4 Z; z 0 6 N NYv .- U' 1,W 41 .4
1I tv..~~-e .~o .j~ :
L wb44 b .494f(Y1 l~4 0% m94 2e4~9 J1 E
fa ti. w i 0 zY-!f VW Iz I i z At 4.3 %1j
53
SUBJECT: SUBROUTINE CDC0NV
PURPOSE: SUBROUTINE CDC0NV moniters the convergent-divergent nozzle boattail drag computation.
METHOD: CDC0NV computes the required input values forSUBROUTINE DRG from the TEM-333 inputs. Ifthe supersonic procedure is to be used i.e.,Mach X 1.0, these inputs include the designMach number of the nozzle which is solvedfor by iteration. DRG is called; then boattaildrag computed from the CD obtained.
Note: The set DRG, SUBBT, and SUPBT were inexistence prior to TEM-333, hence the incorpor-ation of this routine into the logic.
USAGE: CALL CDC0NV
Input through C0MM0N/ABIN/ and C0MM0N/AMAX/Output includes D for interference routineFlags PLUG = 0.0; BTTAB - 0.0 causes thissubroutine to be called.
SUBPROGRAMS: AEXHST DRG SQRT WARNING
)
54
1%,I
ICON -1I
Do j j_
09I
Di 0 9(DBM) 1. + S- I U -
L/ D9
[ Diameter for Inwtference DragDs" D9O0, *
< .9
Solution for Nozzle Deign Mach NumberNewton-Raphon Technique
Find PSIPO Ratio Such that AIA9 Equals
ha of Input Performance Point
(FUNCTION AEXHST)
I - 0 00
X -1 P/Po
X2 1- (PS Pdo
Figure 8: FLOW CHART FOR SUBROUTINE CDCONV
55
• +•'.IL, t i .. Ira
F~m AXHSTIX2)- VA
556
F1 F2
X2 " ePD
F2 • F
50
100 MDu 2(/O Y''
CST f (DMhMP~P. .y ICON)
110 'r,(CALL ORGI
DST = CD'0M
RETURN
Figure 8: FLOW CHART FOR SUBROUTINE CDCONV (Concludedi
57
JI I )of I I
j'1 1 Iia JtoII '16
jy a, 0,1 .
0 ILI
a.~~ O'. l
in I.
I It4 1 Wo 4 2
V.a (A IW , b
.56 .1I 0I
z~~~1 LO0,.0Illy ~0 Ijc ,
IL I-I
41 4, % :0 - y is*I& 4 14 '0" A . -4 vQ T311 %Q 11- -e ftI I ' 1 0%*
AI it I4.4 0;. -b KW
40ite..- ' IVI g7,4
Zv --. 4 oI f A002 " a itit11100 ---. . of -4~ -4
% ~ ~ of 4 * I I 0. I0 of I II If 66 . j ý4 0 -
a1 1 1 . .. 4 N -. . i _ , p 9 1 1 U . d Iý N . N * d 4. C. )
~IO C 0'0 405 1 Y 0 n,.I 4 M.d 6. *. W X 'I A. ~- 'L k-J U' P.I -I..44NN0V~0 )K0
pq 44 4CI .1 4 .4 112
C9 C2.)I31 .) f9Irlat It ,'1~It Jti1 u~, U ItI'*1111 .11,1:jI.I 11
allJJia %JU La J 4 W0 a a - .a A L k L2 J_ ,3 jo0 t (jSI3jIJ.
0 MA .4 a IA
I,,a .0 a4 0
a aa ai ao .au 'Cs c
(.IL
In in
ce co .4 94 P .11'tA I.-. & tr)E c,, c, %.4~ ~ ~~C ff ' N 2Nm~%
ay am a a Isae0aaz
2 -3 -9 I CL~
LS 43 fu' '. i
4, 430 .4O-
a Yt 3 1 k3a C4 N ca Ctij(4 2a sN r)3 tj%4a 43 V'-
C, , e4Ie3e
All * 4 xfl0
v4 L% .4" A'o (, ' -Ro-
%.83 C* -2 CA Za 44a %3'J ,.4 .4.4 .4.4c Ls Z4
4. " X.- .4tin '4 0- 0
00
fy vM I~ 03
59
SUBJECT: SUBROUTINE PLUGMX
PURPOSE: SUBROUTINE PLUGMX computes boattail drag for aPlug nozzle, mixed flow.
METHOD: Boattail angle is computed from the maximumdiameter, exhaust diameter, and plug length.Then Mach is checked and either the subsunicor supersonic method applied. Input tables4.2.2 and 4.2.3 support the supersonicprocedure. Boattail drag is returned.
USAGE: CALL SUBROUTINE PLUGMX
Input from C0MM0N/ABIN/ and C0MM0N/AMAX/Output includes DS for interference routine
Flags set such that: PLUG = 1.0
FLWMIX = 0.0
BTTAB = 0.0
Will cause this routine to be called
SUBPROGRAMS: AEXHST ATAN SQRT
TABUl TABU2
60 •I
S• - AEXHST(AE$.,gPOqo)
D -.
- T --1 1.0 - Cxv
DB,0.0 DBT T0.0
•~>0 .0
CDp 1.4 Tan (0) 10 -. _1 CDT f - (Mach, 0) from Table 4.2.2
I ac 1.53 AMXCV* f (PsP°) from Table 4.2.3
DBT, Cop10-" AMqx Cp ý .- "_HEPv
CFgeoa CVp_ r. !O AmexCF -Cgaoi
DUT a (CF g CF9 ) F9,
Figure 9: FLOW CHART FOR SUBROUTINE PLUGMX
61
I0 j
ItI10. .
n fil
NN
a Ua. J 4 f
02 'A I 'NC am &Z94 .4% wC
C0 a~j VC
*Uj 1 C
t.- B .- 9 0. 1
ewlw 0 11 0W., 1 .* 0 Id1' .6 tIC 1 ; . - 1 X Y
z .9'.99.T 11.- CUis
~2la s-1 -1U4 is ofif -.1 43
~i.44.4JNC~jI4.2 * A0P.i,
IJ9 I fJ~~33'o JtJJ-'L.Ii(INi',
fal2l ( YNtv* I M414 M 1 nNW 3 . 4 8
62
Q 4
.4a 4 ' 4
co I
(C W',m W, .1 .I
40 0 -.
C31 U% .4 45N 3 2 .N - cmesa 42 4m419
C, 0 40 a .,42 sCOC a a'A 4 1 cbcsC3 3 c (3'U 42
11 N* a,- b4 P~ad af.a ~ Ta
a3 mm a #a3oaaa1. 43 . f. o r %D aaaq .3 -ton
1 0 C3 1 0P! c 4.4. I- i.a CI I a. es
fI N. 40' 04 Ca i -&, M 02
jII
44
;A A 1A
z wi Wij 6hi Zt3C2 c a C2 3 C21 A~ 14 'AT Ir od 3..a OI F"lI- @4~ thJ * 2 1, (3 -
1,4 U% r2 vo 3P3r .43( I.4 mC3 .4~ rs 4o 0, f
-j 4 II qb, LaN 0 J~I .P ~ 4 OC' W W#iý )%Jr'I -9 A A 0. '43 0 3C 3L 24,
It I' I iJt~ I I-IWf
4 3 -y e 2 1 4
-63
SUBJECT: SUBROUTINE PLUGNM
PURPOSE: SUBROUTINE PLUGNM computes boattail drag fora plug nozzle, non-mixed flow.
METHOD: Boattail angle is computed from the maximumdiameter, the exhaust diameter and the pluglength. Then Mach is checked and eithcr thesubsonic or supersonic method applied. Inputtables 4.2.2 and 4.2.3 support the supersonicprocedure.
Boattail drag is returned.
USAGE: CALL SU.R0UTINE PLUGNM
Input from C0MM0N/ABIN/ and C0MM0N/AMAX)Output includes DS for interference routine
Flags set such that: PLUG = 1.0
FLWMIX = 0.0
BTTAB = 0.0
Will cause this routine to be called
SUBPROGRAMS: AEXHST ATAN SQRT
TABUl TABU2
64
Am AEXHST (AES ?pP, Peo)
Aw fa AEXHST (AE18 'YF, P1I/Po)
9- irT. i DT- -
C CD0 . 1.4Tmn(19) -CDT -f(jMach,0) frorn Table 4.2.2
Mach153 cv f IPSIPo) from Table 4.2.3
DIT Co 0 ~gjC VD ' f (P16/Po) from Table 4.2.3
VE -0.5 (CV + CVD)
C P 1.0 -(1VCV
CFggo . CV..CDTO0AMa
Fg1p + Fgi~e
DST, (Cpg CFgv) (Nijp+ Fgi
Figure 10: FLOW CHART FOR SUBROUTINE PLUGNM
65
06
10 a.0. w 0
14CY
ts 11-
,at! 01,cy th
;.4a.fy1c; a; x 04
z for I.- xty
40, ox 1.- .140 z
ev C; x 4.314.3 .9 "31C b..
bm, 22 ell -C 0.3 ty " .1,j 411 .2, 3w i). 94 0 IM 6.4
Awl 0 s- Z f: "I- CL K Ia10.10 -CL (L If.
w CO 49 .9 W 'N In .4 uj I- M
49 z4 IL N &. '9:-a 43,2 a .4 w m , ý 'kaL IOL4a N rZo 49 - af 0
:0 -L (A J -4 -4 ta.& dw Ili I" w 3 -1, 31 1 "'Il ýNft 0 0 X 9 9 A A4 allne 41CJNM x 1.- 14 x 0- 't 6mu.-IlIZO 1.- 42 X X 30 ;.tL b. ILI A r 4; 1.- 0 2 -
al .ý I X "1 1 44 4 w 0- CD j 19 N'Z 10 0. 1- "1 "1 .6 12
49 C:13 11 w m w uiw -1 1 m C2 JIM 0 w - 0 W499 0 r3 $A W 4 04444ox x 6- T 00,1670
z % %. % % Z: gý* 6. i-C 4. 1 .4 ,; Np a 1- 0(L 9L %4.2 (WI %4 "Is , o wC - w at 06 -4,6 (5,1
19 w " IL L IL I) L"64 1 w i " .4L, %lC ; '.
2 es VIA fA 10'M Id Uj W M t.ojeft for w 0 9%. lu, 0 03 9ý N .4 .41cl 0)m 49 .9 49 W 49 1A t3 I a !a b. A. .111.4% %k % 11 it of of it U.1 K 0 .11 N
2 z U z I z z z b- I- IAJ.411 0 x J -i A qg 44 44 of j zrj vof
IZO 'Aj 1.- 0 6- -30'2 IAJ I,# (A T 05 "10 -3 "If 'v IA IL 10 -. 1 it
C.) 0 130 -6 'A -9 '31 0 6- b4O 4 6-4 U 1) 11 It ) If If 'IT Ur3
rsIs
4A
N cu-tv CY tyl W 1.3 96 f P %0'-a %3 .1 C3 u. a'm ly r, g- NO -M " " r 4 t t a k, tý . .4.4 .4
-,1- .4.4 .4 .4
12 -1 12:3 tj -j .2 Ca 11fm , 412 , a cj " t-l rs %3 ca C3 '3 .1
42 92 ý10 Qý %a ý3 U %3 ta Li %3 14 %7 43 .2 %, .I a Q 1.1 tj L3
66
.4' Im a y "( 4%a 4M . I a 4P.1
fa c It I'r$ Is
ILty-.
fl -4 VI% 4-
I~~ 60!~tIt. tv 40
to (AV t C pe) N * %2 t3 CM A -
N j r. -Z * *W IbfZ - -Jf% N 4 40 S4O w r h to A
-4 1 4 9 w I w J%0 .2 4A 'N24.-4 q 0 61.4
es Q. .Ja U% .Styria q4 3N%0
Gi a y ao jf' U' . .N4 a lt, t 4r jE 4-.r "v6
I 3 m I C3. ca. C343 -aa 3 a*~f 12 a . b W 9 ~~l6
IA . -"2W $ O U.9 4 .J: ~ f3N. 2-0' A IV 4 '0aw
Z~ 92 'JC oJC ^ u%4'. i'n '' .q4 5 .4 W4.1 'A Ci. IAJJ~C)~I
'c to 0 .4 In f/9, IfN0 ft2e1'I@ 2f21 0 6 W OII.-. .,F 'S 4yN.-
'3 P% 0 U%''j N -. V . N cS41 -- '.% le 10 V .'1 4 N t9IS 6T 4 .4 ~ e%. esN -- 9.i
A.. "J 0. -.02' t 1'4 . -.2 S . tbt'A 4 U ~ 'V.4 'V3 'Aw t, 'k.4c ca 4s C3 '11 ". g pm C31 6 ..2. 4
z Iw oj 67
30 Ol i?. x z N i J 4.
SUBJECT: SUBROUTINE ABINPT
PURPOSE: SUBROUTINE ABINPT reads the nozzle performancedata deck, cards 4.1 to 4.2.6.
METHOD: The input deck is read. The thickness of theannular base is doubled to account for top andbottom when compared to the total jet diameter.If A10 was input the table of Mach 9 vs. A8/A9needed by subroutine CABTAB and the Ps/PAMBlower thrust are computed. Tables not indicatedby the input flags are not read.
USAGE: CALL ABINPT
All COMMON blocks present are defined bycalling this subprogram.
SUBPROGRAMS: TABLI TABL2 'rABL3
68
TO; "4 ,,I'
A w
I. IN z :1a
T - .4L&4to a-
14 Iw oz 319IC b. #11 .
.4- a .40 4. 19 Ca4 col N Iw 10 1. 2 C2I IJW 6
0 z
g~ .4? ** M w93 6 'O -4 1.- go CI l
to VI Z' M. x 0. . M
K'e *N a a 3I.- !J (1.* 9Jz104'4.4b. 4 4 09- *fda s 1gN41 EU f5 -2 %'. *
Mlazxg-a 1W9* . -:: to40.(IO N~.. Z so -4 4O 11 ja N of .4 .111 cl - JtMM%4ab w' '0~ua ::: Y.. .O 0 n0 js .. K 0 .. - ý .1 1; 0. of .4 C 01U
11 M.. x M oj x c-h '0 M 1-a 1- 3u A091,z
r4 110 0 .4 f
N Yt yN(M% *NNI "N YW N -- cy0 fu0 N N -iNN ' .NN'M"i :'0 *-' N's .4 t 7 I .0 , 0 21 '03, 4 44 @4 4%~ J 's.4 . *1 .14 .1. 4 -4 .J . 4 .41. 4 Id,
.4 5 43uI' S 1 j t2M .2C tI. * ' .4sa 4 .A3 *fl 'J" I- -
44 01 0.84 21 44 4 w B CW .310.4.3' -r.I f'> L ly1N44 444s-444g,1e4cm 1 A.112O - 44* %.31IO'O
69 , n j4.4*. '~'4.*.f. F*.
%3I
4 % 4 IL
x 14 j )(a
ki. x A
OZ N 2'ag
z 0 49W.
a N
II.4 -a
., Z.4 Z 0
on-9 046*-
01 ~. 1 CNl .-4'bS m
N'- I. 2 J -. 1; W41-4=04
ONco 2 . J 'i40NI Jla
NI b.. p 4tL'*4 .W - ,W '4
wIU..0S'W1
'41 .4U. .- * a v .(Wb* N *ZWW6'
no, (s i-', .-- I
2j Au j( IA b4A. JIL4.I
Z j
Inell
.4 Q4Il . o I .w"NF i
4~ hI I
ILI
I., ca 000.4,NP~~t. 0 UI~ U UU
.10 C3 .4 4
.4y4.% Q13 Ma I1 0, coCID aC11 W 1 em m0 a1., C C"0
0,, 00 .34 Ono
0430il Uf 3 Uc c CIO@0
0e 2 cy r4 -. 4 Sy*-41
.3. r% 1 4M4 MN . 4UI J
4A3.
404@AJ %a 0 N x.4 J) a z. N N a,
-4 2 I"N I
:1 W1 W4
a-- -44-j~0
z L4'j es1AJ - 0-1
IJ W~l. :. 'I
'A I. @04 ',
Il zS~N t3. -4s * 1 @j, ZJ I* ~~ ItP)c I. I4
z .0 d~ 2.12 43j .1v '13.31 N
N~0% 00 0AY 2In UJI'42C3e Wgj , eggs,:.2 1. Z I
(3W .4I71
SUBJECT: SUBROUTINE SUBBT
PURPOSE: SUBROUTINE SUBBT computes boattail drag fora convergent-divergent noz7le when Mach < .9.
METHOD: The quantity Dj 2J B . DM)is tested. If it is
greater than 0.25 boattail drag is determineddirectly from built in tables XI and XII. Ifnot, an emperical method to develop base andboattail drag is used.
USAGE: CALL SUBBT (DYDJ, DBDJ, EMF, PTPF, THETA,
ICON, GAM)
DMDJ Ratio of maximum to jet diameter
DBDJ Ratio of base to jet diameter
EMF Free-stream Mach number
PTPF Ratio of jet total to free-streamstatic pressure
THETA Boattail trailing edge angle - degrees
GAM Ratio of specific heats
ICON f = 0 circular arc boattail
1 conical boattail
SUBPROGRAMS: CABTAB TABUl TABU2
72
CDDU C +AD/C I )I
Di :M2z .3
- )fro~abelXCP 8 -t~9D~m f4.25le
Fiue1. LWCAT O URUTN>UU
CDZ (0fD/D)/DnD~73"I
0 8m -1m
( Din)
COS Dg n '%PZ q "P
[ CD % Js
fj > P 10 Aoo~fortable >II mU C/O ST fCA/A
.0.
74 0
I I
La I.I
94 -4 w
I- :
J' .4- 9
ee 1~~I4 WA0-~' 4t9j. 94
oa D.i one
z E I- 9 3c
I- X wS 2I- CP . Z ( N
a10- ~ ~ ~ ~ ~ ~ ~ I If- a .MaIn V1.9 UZ kh. ;z 0 0:4 r
P3 o(I twtb;3 I %1C4 U4 1 4 4.146C 1
0j Za 6.. 6J-i' 0. (L a ~ toLI 33 0 1 f31 TL.i~ *J1 13. I .U2S
ta 1 1 T.b.76
td
1.0 100-1
0 14
U. I
I a. o1 , IP3 m .4 es1 n-41
*N I -I A aZ
0EJ M,0C t zI.ý
Ub.1& . 0 9.. as - 2 .
3. cyi IA NLn
.~j 9% 1 A1%,I
vy f* III 'yfP4)y `.NiIJ JN ~. N'~J '1.2~
) pi IJa
** a It4 00 IN o I tvU I f %t mO
Pv 0 cmmC i"' c I
ol0 ' IT
I 0 *o~~00000006
P. m ~ U UIn .. 4N NIf U% U
aa**.4D'-.4.4m
10 ca Q x x P. I& x . 3. "
043 ~ ft 0 43 0.N.lS0*.NN*D C2AI
00 N0 0 .4 000 @)' C2 43 -1 s '20j I " 7 4.00Nfyc 0) 04 a mo. N00 00@2@0 *U13 W 1 Y 0:
f% In 44r.
:. * 0 0130,$.@%1% t l M a0
*A I. i UUSO. UUA PUO
2 AN. w I ;'S eS r? C3.J-1 '1)I4 1M .3 t - LN 4
0- x .MAIA 4 N¶ N t% A f.. * A.4 . -f%.0-m ., I
0 ts 10 *2h UN 1. -3C1& 2 3NN..00t 4= . o
N41 N0 111 0 09a a. elm re13((10 3 1)
03 b S* a *4 NgggItgjggtgC*-4 % % M*:,S
b-4 Ii b.- I- N
0!z I1 IA I 1 0 20' *'2"0 ' 0 ~ ~ ' 1i 6f 0 1 t
IL on -64N P44 4 '1 ty2I I "tfN ~ , ' N- Il W
Iii 14 IA: J.2 I~r 4.n . 2L*' 1 114J .J.J..'tt .4 11~ I
,g cc c g e - o - 4
in '4 A 29 9 9 hIoSS3 4aA 0 -1- J 0 V
77
SUBJECT: SUBROUTINE SUPBT
PURPOSE: SUBROUTINE SUPBT computes boattail and base dragfor a convergent-divergent nozzle when Mach > 1.0.
METHOD: Boattail drag is computed using Table I, thenif a base has been defined base drag is computedand added to compute a total drag.
USAGE: CALL SUPET (DMDJ, DBDJ, EMF, EMJD, PTPF, GAM,TANB)
DMDJ Ratio of maximum of jet diameter
DBDJ Ratio of base to jet diameter
EMF Free-stream Mach number
EMJD Jet design Mach number
PTPF Ratio of jet total to free-streamstatic pressure
GAM Ratio of specific heats
TANB Tangent of boattail chord angle
SUBPROGRAM: AL0G CABTAB EXP
SQRT TABUl
oi)
START
< 1 . (.. . ... .... . . . . - ,•..... . . . . . .... _ I
(1 B°° -, f(•othe~
G - f(Mah) from tal I [CALL (Kr talecost - 6-ton-(P)
D MM , ' 2- - P -/P F
< 1. (2jo -- .$4MDo
P il/P F - f ie .11115 1.1 5 2 Mt
in.2 (2.) ..Q(ua2.1
CDes ('_ F" 1.-.(IP- f (C) 0,from taleI,r'M~h2r ( D-j• PB/PFK f (K) from table II I
-DP PB/PF 8
M ach * .815 - 1.1 ALOG(K)|
y Mach 2 (D) 2
\Di
CD -COST + CDs
Figure 12: FLOW CHART FOR SUBROUTINE SUPOT
'7a
al. 1 I '* I-
0! . I Ia. Is
I It
alI--
.4 1- 0 a- ~
1 1"a h 41 1bi
*I 4P,1 x Ps-tab 2Ix iv 1.!;xZ I
.4 .3.I.4AIZzT: N~,U 11-4 Is N
W4 . 1L4- X a .49 b U % a 10 on 0 1-2'
N1-I~~--t. 0 0
a. 0 1.. -DZ 4NX1- N& 11.64U. 1; . 4 4- - - l
0*01 mom I %.04
o11 11. 1M- IaZ &jO& 13-
0.& sit.-. 1gZa
Is.. j 1 %110..,- ! .4I.I#f J~aIa -~ 4111 3 :- I.;"3..2444 IS It ,h Z!,.
B. .4;. 01b .0 =o8 X4 0 .4 6a r4III j l.4t of 111 1 ' '.t -w4 WS 'A~ Is- 0-1 *04%&L6" 6- 3
%j I ne I"s 110.310 *4 0 t 0.k . 1" .v & Q jV 4 # ( % J " ,
30 N% 4l~ CY a 4~P .4.4-." I2 ZM F)1A 4 . 111 R 4 A~ 2 0 f1 3. I.J f 11%w . eo .N~ 63LP4%L.4 4 . . 4 4.4NFY I n.I t r Ir ?4 -III if% gg 'f 'iI " ll 1111. 11 -1"It .1 c jh J j 3 'j) LAP v:.. 'Al I- 4d -4IjL f #'J0 1 1 'd a.1D soa --f L f a0 2 - o
el 040 4 * ;s 0 %4.2 I .ge0'9 W#2 _1.0 -3 fl0 .31
.111= 4:1 -1 toCT 4 ýj CAP 3 Q 3 S
I so
94P mA!
U, # j% -r cy.af:yC 4U 1c r"f oe
.4 mf a a clIto
0 N am @***-a N a
oe %2 US = cm 11aa0 amaa C, a~ua L
co Vaq 14-
CD CD 4 -.1dda *f% N f s .4ft"s (Y Ca11 %a aU .4 In." V M1. t 2C 3* CI L Pa m
8 0Ia11:,aata 43V CI ao2 a t' a qu %3 42 I's
A.. 0. 4 .
us -2 ra Na IT -.1, v 12 -
'2 6- J ca 4aN 03C2'4*3u t .4NN inAi- -. 4 I)t'",,C .4 oft 4S C)JJ ' ZbD'3 jC 'f%,t ). M $-).IAN.J Zý41 j A% a m Iý,wwý A aw"%a.. A t
Is z 'Is5.5W) S
.4 4 M m ',aa (9
faCI .4'A V% .' 0 0
SUBJECT: SUBROUTINE DRAGAB
PURPOSE: SUBROUTINE DRABAG monitors the afterbody dragcalculation.
METHOD: The input array is transferred to the afterbodyCOMMON block ABINP. A check is made on Machnumber. If Mach is equal to zero drag is setequal to zero and no further afterbody calculations
performed. If Mach is greater than zero, boattaildrag, nozzle interference, and base drag routinesare called to compute the various drags. Thetotal airplane drag is returned for nozzleinterference and base drag so these are convertedto one engine values. The output array isloaded with the various CD'S based upon areaAMAX (drag may have been computed using adifferent area).
USAGE: CALL DRAGAB (ABIN, ABOUT)
ABIN (40) Input array
ABOUT (10) - Output array
The input array is defined as follows:
ABIN
1 AE8 Primary nozzle effective area - in 2
2 A8 Primary nozzle geometric thrust area - in 2
3 AE18 Fan nozzle effective area - in 2
.24 A18 Fan nozzle geometric thrust area - in
5 P/P0 Primary nozzle pressure ratio
6 P1 8 /P 0 Fan nozzle pressure ratio
7 FGIP Primary nozzla ideal thrust (actual mass flow) lb
8 FGIF Fan nozzle ideal thrust (actual mass flow) lb
9 PC Power setting
10 GAMMAP Primary flow specific heat ratio
ABIN (continued)
11 GhANAF Fan flow specific heat ratio
12 XM Free-stream Mach number
13 PAMB Ambient static pressure psia
14 Q Free-stream dynamic pressure psia
15 A9 Primary nozzle exit area in 2
16 A19 Fan nozzle exit area in 2
17 CFG Nozzle internal performance coefficient
18 DHEP
19 DHEF
20 PLUG Nozzle type designation
21 FLWMIX Mixed flow flag
22 DMAX Maximum diameter, in.
23 THICKB Total thickness of annular base, in.
24 ZLPLUG Overall plug length, in.
25 ZLBTAL Nozzle boattail length, in.
26 S Nozzle centerline spacing, in.
27 ABASE Base flow area, in 2 .
28 BTTAB Boattail table flag
29 THETA
30 XDNI Number of nozzle interference spacings
32-40 Not defined
SUBPROGRAMS: DBASER DBOATR DINTFR
03
ARROUTUT TOMINU
0?ZERO
(CALL D8OATR IDB .
Compute total A/P CN .
Nozzle interference Drag.a D:NIAA/P CBS
[CALL-DINIARI (0oen0
LoADut toUtPUT ARRAmDArag DBT+DN
DNI DNI / (No AMA )
CDI*DNI,/(Q AMAX)
Figure 73: FLOW CHART FOR SUBROUTINE DRAGAB
84
b Io
*w w
igit IOf
Oct-
;1 'a X
04ti wI% L -4 4 9 O45 I -% 9.4 .4
w w 3 1 * ý ,b-I L w U I d'1 (4 % I 61
r* -I4 "J *
.4 . 4.a !
52 49
"t- 129- f-%, 1 0. 4 " J- UN
V2 I3 'mcs t31 1 1ej " 11:2 1 * -.2 001 4:2 In %3001 I 2 " . s1
* Z a 0p CPC 0vL a* a 2- 0 c 3
,4S@J N.4 9.4 ~ as
w
c If If
ItI
o oz"o -, -2
W e
C3, 1 C3 C3 GC2 C v a4
a. C24 CC, L3 v,02 I
'UL) CO Z
Ic w U% a.
C3 .0 -z; '-. -f"IA a ' 3. a D a f
~~Vw M, aa
a IAIa
J,1 UltU
a 12 2 a
, It
, ,, * (A
1-4 M .II~ L "IU 1A 04 LI
220 3 - Ls (4 AjN ' U* 4i 0rS-.a -Ai 4C3 (A C t2~ ýaa' 4 .10 La
0.4 b- Ut) Zi- ..
124 1.- /:I I~ I IA'j~ l I laWIN 4 1 D 4o N of
Il C, 2 lcA 3'
01.0 t V 1.
SUBJECT: SUBROUTINE DB0ATR
PURP0SE: SUBROUTINE DBDATR monitors the calculation ofboattail drag.
METHOD: The input flags PLUG, FLWMIX, and BTTAB areinterrogated to determine which boattailmethod is desired and the appropriate routineselected.
USAGE: CAL DB0ATR
Input through COMM4N/ABIN/
SUBPROGRAMS: CDC0NV DBTTB PLUGMIX PLUGNM
85I
START
<0Mach DOT 0-0
> 0
tabular Yes CDOT 16 1 palated
option? from tsWe 4.2.1(CALL DBTTB)
No
plus No CALLCONVERGENTnozzle? NOZZLE MODULE
[CALLCDCONVI
yes
MiKed Yes CALL MIXED FLOW
Flow? PLUG NOZZLE -400.MODULEICALLPLU
No
CALL NON-MIXEDFLOW PLUGNOZZLE MODULE[CALLPLUGNM)
CR:E T U R tN
figurelIP: FLOWCHART FOR SUBROUTINE DBOATR
89
IS 43
:"or ji'I
".4x I
j W*44 (K00j 4T.0~ nI. -j f
z ji I- n(
lt IL .8AA.J, Zx0
4%e*8 4u .4 j 003 v, r, L3 -,10 1
N ~ ~ ~ j -W4 *.108 jO .
m x~U)a 0, 1 . C .Ix i vJ$."
545thou 1.0JJ U c
(3 .Jy 6- w)
30 cyf Y"$ 1 Y AA 0N CP.
-1- 4.4 fh4.4 1 ILS ~ III UN2 I'l" J t tkOLO
esD N1 M~AE . Is~ j;l kr.0 L3, "I':NI
910
Ic U P
Sioil
co t
1..
Ic IL I
Al-
C3Cka.
C U ,
CD
.1 N a L7C
4: C3 ca C
49
2 3 jj.41 CC
Nl i Z toa I (A '. jU 2-3 0L
K 21. 4 1 Il `3 4 U Cto Tn 04I I4
r232 . 0.las K4 14,I Z aK Mt .1 'A
I.C z ' ot L 1- -
ct4 W-.11 1 4 0 w3 I' I U
US w.
SUBJECT: SUBROUTINE CABTAB
PURPOSE: SUBROUTINE CABTAB computes afterbody drag as afunction of A9 /AI 0 , P9/PAMBI and Mach.
METHOD: The drag coefficient is input in tabular formin input Table 4.2.4. Mach and A,/A, are known;,
.; J. 0the suprogram computes P9/PAMB after interpolating
Mach 9 = f(A 8 /A 9 ) from a table generated by the
program. The table cenerated in the inputroutine ABINP is developed as follows:
For Mach9 = 2.8, 2.6, 2.4 ... , 1.0 compute
+l+1
As/A 9 = My+l) 2(y-1) Mach9 (1+1_1 Mach9 2)2y1)
The resulting array of A8 /A, is strictly
increasing; hence serves as an independentvariable array with Mach9 as the dependentarray. The subroutine also checks P8 /P0 against
1 lower bound value of P 8 /POLB = i/(
The C DAB obtained from Table 4.2.4 is based on
an area A whereas the program uses AAx (most10MA
of the time these two inputs will have the samevalue), consequently the CD is ratioed by A10/AMAX
before returning to the calling program.
USAGE: CALL CABTAB (CAB, AM)
Output CAB - Afterbody drag coefficient
AM Free-,stream Mach number
Input from C0MM0N/ABINP/,/AMAX/,/AREA10/,/P8PAL/,/XMACH9/, and /ABTAB6/
SUBPROGRAMS: TABUl TABU3
92
99PA
pW~mb'o 1.0
M>h, 1.0
CAB/A (A/1.0 PP Msch) frm1a.0 4..
f I CA.g A1 0)frAm Inenil
;p 1.0nltbe.FrM c, .8 ... . .
42±~ --
FCur O 5T FLO CHAR FO UBOTIECAA
AMA3
X aa
I * J toI
4;~
as 0; 3
64 .d *
.4 1 4~.6 V 4'l :
on S %p t -S
or 00~ 0 II--I
z mU**SEc, s Wl.01* 4
"'.~ a ~ .raI '6- 22.44at 0 I 5 b-F
* ~ ~ ~ . .4. J . (t Ij4 -2t o L
1W2 ~ , I-4 r J 4 f a % %. .
.4N94
W�.
V - - - -- ________________________ ,.------,�-.---.---. t
I j I � j II II I
'IL 1
�. I
I *1
I I
I I
.1 I
. I
I. .� I
( j 0 1 I
laDrv 4 I
I. 1.hi
. I',41 . I
J IU
4. i
� aJo
' *'I Ihi.
'5
0.4cul ulE U
10,1,0031 02
%D me b.4
o I.- co 42.0b
%0 ty 'oIto~
C3 r% caW 01
CD43 .40CD.4 C Ca
00C,000
a C2
C) N.4 t3.4N.40.
4.3 C, ¶4 Ca -3
b a z
la LP 13 603If
4* ?N' 0 *L 94 a O W) .)J Cl
.2 e'i "'' -
AS6. 6-4 `3l3I r.0 .IJ6 .4~r . N a IA w~
z W 0 fj M, C3 S -. $ . S ýSIS z
(A 9 q 0W C C ra02C39m'
II
SUJUCT: 'U0TMINi DINYF
PURPOSE: SUlDWTINE DINTJR computes nozzle interferencedrag.
METHIOD: The ratio S/D is interrogated to determine ifit is greater than 1.0. If so# CD isinterpolated from Table 4.2.6 and total inter-ference drag computed.
USAGE: CAL DINTYR
Input through CONUON/AJIN/ except D which isinput in CUI•N/DIPACGI. D Ws an output fromthe boattail routines except when C is
interpolated from Table 4.2.1. In this lattercase D B 1.0, then nozzle interference dragcan be input only as a function of Mach andsome constant S/D ratio where the rat.o isinput instead of the nozzle centerline spacingfor variable S.
SUBPROGRANS: TABU2
97
4-
START
F 16: FLOWCART 1.0 O T NT
'S
a 5-..-. - toJ•..%•-
f- - -it. M -=.ON
R MN
Now: O €omped by boattaN drag rouimn
FO"• 16: FLOW CHANT FOR SUBmROUTINE DINTFR
95
Iw
I-- 4
NNf.4 14I,
44-
lob a a
w*U.*0 '0 a T
0; ft I4 t3
04 W!,c~g2w m
sI~
Ni' 4 .4 %J
*'x xzi i, aa
Z 1 04Ie3LtvO02
54 .8 4 .4.
ty (14 Wi..N3. 4
M 0) U%.4 Aps CIO .4.ý4. 1ff
4a CIO~ CIOf La a is -
U 4SC~99
ca 1
Im .4 I
I .I 1* I: I .
C3 0 0
(Y4
oft~
.4 .tO t
izI jl A J q L %
:,a 'A r3 * n 4 I
a ca I Ac
4 I-OI
Sw
'. .4?& 1. V b - z rc
*100
SUBJECT: SUBROUTINE DBASER
PURPOSE: SUBROUTINE DBhER computes total airplane basedrag.
METHOD: If a base area is input the base pressureratio is interpolated from Table 4.2.5 anddrag computed.
USAGE: CALL DBASER
Input form C0 0N/ABIN/
SUBPROGRAMS: TABUl
"101
START
N ot:SA041 is Ynt 0ififdootr4. .4
Fr7%-1SFL CAR SUBOU
2Pamb
oil
Note: ABASE is Input In field 8 of card 4.,1.1
i ~FigurelA7 FLOW CHART FOR SUBROUTINE DBASER
l ,].02
, to I I'
I..I,.9 C
2 La.! 01.-
a *
0 LIA -
*q -4.W* 4
tyN .W1 ',
1' Z ~C4I. .40. 44.4 *0
* P' Ma 1.)' ma Oi10.4 ~. "'a %,g 4b
a2OC 1 coo
a aII V ;
z 1
'S CN ;mCOD L 2 2 2 ' 3
3r.J
Ip CS CoiI
ca c
1-0
130 rI N 2A u0
z 4-3'111Ix iw x il J Ij (% U 1.-
ti CtN " in n ib
J c 2 9-ca '5 14d13 1.-$2 M~ t3 C3 8. 6.
#A(A) (A3 CY0Cl I
w 1.2 z w ' I. I Ii L AO.J U ) 4J ! 4 I.4r' 0l cc' u
2' z~ ~I- t 3 v;- 0-' - .
tI (3 0. j U 0 A 1 , I J 47 ty 4 C2 og a aLC2 .1 418ýx 1. . t
'RikU
I I 9
z CDt
j i
C3 Z
WZ .41
*4 m:l - 4
N N
v. 150e! -
f3 x
cc #V -.94
Ny xE4 to 0 0 ;
0W44
~~Ls Cal i -
d,1 If
I~c EI*cInII 0;0 0 (3In to5
I~ I o
aa.
0~
(~01 00
a i. 4
%3 aI aSIn S.4 -1
100
14 1
14 64 ILIW fA2 2 3 e
4 r - -40.42 1 .. .4 T 4
4A o l 9 .1 04cq15It (
W 49 f- IIA r4 i
ly' z I I~4 I4 tt4" I -
10O~I ZY z .10 .ty LI C3Iofj -w 4 I.L Z ia 91f3 La
1046
.SUBJECT: SUBROUTINE FIXDIM
PURPOSE: SUBROUTINE FIXDIM determines the dimensionsof the nozzle throat and nozzle exit inputs.
METHOD: The input flag is interrogated and three flagsare returned indicating input type anddimension.
SUSAGE: CALL FIXDIM (FLAG, J, K, L)
FLAG - Input code value
J = 0 area input, = I diameter input
C K = 0 inches, = 1 feet
L = 0 ignore, = 1 (A9 /A 8) input.
10
107
a x
eq 0.e Ir 4C 40
6.." jI ~ .. .1t0 .42 4 1. 2- 0
I w 2 3%
I I Los
- ~ i
44
I F
ty in
,• ,,
I I
z w 6 W I..
I ft
I I
1*0
on F
II " 41 . o -
a4 4 -P .3 I1a U. w"4m I t lD oi b wA Oit 0' 1
I Sa K 15 , wi ~ 109
SUBJECT: SUBROUTINE ATM0S
PURPOSE: SUBROUTINE ATM0S computes ambient pressure andtemperature using empirical equations for the1962 U. S. Stand4rd Atmosphere.
METHOD: Altitude is tested to determine which regionit is in, then the appropriate eqaations areapplied. If altitude exceeds 100,000, anerror is assumed and altitude will be dividedby ten until it is within the required range.
USAGE: CALL ATM0S (ALT, TAMB, PAMB)
ALT - pressure altitude
"TAMB - ambient temperature
PAMB - ambient pressure
SUBPROGRAMS: EXP WARNING
110
II
START
Twb 618.0 - .0=03618 ALT
518W
-I
>Io
Twn T - 364.18 + .0006M3 ALT
ALT: 10002 30.4757 - aG43Tam
> 100000
it IiN
Figure 18. FLOW CHART FOR SUOROUTINE ATMOS
*1 111
* :1
00130T 300.00
I'I'
W1
It -6
.09
I- w" o' 4
.A
#A c 4 ca ey 0 *
.. b.a * 'd rf f -1On .% *.f ON$.
o On* , - 0 .* q4
0! 49-4 0-N 2. J-i
aj 0 0 w a a J 11
P4. .4 .4 .)-9J%.
N .4 .4 N A *ý, !:. oLa6. f0 J *i ts s"'I tjJ
%aS co 0 N .4a " "9 l -iIj 11% .q2 3 I C * t 2 % 6.2 2 2,jL Z .3 a C
t*S9-0 * .~ 0 6-.40 '~112*
0 I0
Iii I I
CD .4 N
f.3.
es IA
I Ij
AS 2 I
p IA
NA I J I W 1 L , i
w - IImetl.4 - ' . 3-CLI .4 N4 3f jf
Of (DV 3 'ACa I I
at~ I113
SUBJECT: SUBROUTINE PERF
PURPOSE% SUBROUTINE PERF controls the calculation ofgross thrust.
METHOD: Mass flow, enthalpy, pressure, and relativepressure are developed for the nozzle throat.The thermodynamic properties at th- throat arecomputed, then gross thrust computed frompropulsive nozzle performance analysis.
USAGE: CALL PERF (WFT, WO, PT80P?, TT0, PAMB, FG, A8)
Input WFT - Fuel flow lb/hr
WO - Air Flow lb/sec
PT80PA- Nozzle throat pressure ratio
TT0 - Total temperature degrees R
PAMB - Ambient pressure PSF
Output FG - Gross thrust lbs
A8 - Nozzle throat(given) ft 2
SUBPROGRAMS: CHKRP GTHRST PR0FH
114
Wf- Wf./35W0
FO% -wlWo
FOA2 - 0 0
H2 HOFT (Tto, FOA2 )
We - Wo + Wf
He8 H2 + 4. eW8
PS (VP/o) ,amb
PRO - PROFH (H8. FOA9)
COMPUTE CHOKER THROATPROPERTIES
[CALL CHKRP]
S~COMPUTE PROPULSIVE
NOZZLE PERFORMANCE(CALL GTHRST]
C RE:TU RN)D
Figure 19: FLOW CHART FOR SUBROUTINE PERF
7P~r
115
06l,
0 I
IL
IL
a#
'W-
a.a.
awl Ila,,(IA T
v IN, i
I IIii
U.
I I I~
01. , 11-.- 0 I 1 . i
Ag : ý! W. of6
14 - if to I of i• i g. 0 x
a -K .9- .,N12 12
S r• , N -I • - -" . .
M.N•'a , ,
(- ,4 -4 4 4 -'-*I *rl a
1.3 li c W LX CI
~'%IS114
-".------- --- - _ _ __ --
Im I
fy V
in .4.4..4.4 -4op~~ CD C2 C2 rsCD
ID , C , a0 C, C
EA~
U~tL 0. -
.4 C2CYmV"
(A I C3C IC,14
in.0
IA I- (A a .2 II1.- 2 1.-
' I En ts -1 Ia
z s z 4 (e
i4 1-4 0 ZO 4~ 1. 2 2 34j-
t ot w 94 UI Id I o0
de 2 : j. IA).( I~ IZI. I I I I
I-4 IV v I l b- PIP 9- -.4I
In FA
0' a - .. C.4 9 i4 u31 3 I. P j - X' x 1$ 40 40 1. 0
ae i a Wi Wn Wo IA ten,,117
SUBJECT: SUBROUTINE OUTGO
PURPOSE: SUBROUTINE 0UTG0 prints a matrix of performanceoutput.
METHOD: The output for NALT power settings at a Mach-altitude combination has been stored in thearray 0UTP. A FORMAT is built t6 print thevariable name on both the left and right of theoutput columns. The matrix is printed and anyindicated punching of MARK II data is done.
USAGE: CALL 0UTG0 (NALT)
NALT - Number of columns in outputmatrix = 10.
Input in COMMON
0UTP (45,10) output matrix
PC0DE punched output flag
DA, TE date, alphanumeric
TITLE (8) run title
MACH Mach number
Output
IWARN Error message indicatorintroduced
SUBPROGRAMS: MIN0 M0D
118
Al
a ft 41 L~- (ý c' . . ..- vs.ca-w-0,--..-
*4 .4 m M" P n"inq",44rr*r ttU%% UL
I CE 12
0. 441 14
IZ I .
a IL ILT
0~~ ~ 0. 00 , 0 0 0 0 0 0 o 0 0 00
CI adjiPA. a 'r 04 W
M= , w
"M It(* a l. t 4 A
?U L*I9 in w - aL0 %C.0 W.0 - .4'
1, 4: 1* 0 ta ;a a, (L of It
I J a K1 4 .-i 0-4 %D I.~- z 1 9 % .- U0J
14 1~ .4 t
'1 .0! 40', 4 12*f. -UIa t- za .1 ja ax (L ~ 0
W~ & S- X, a 0 .on v!.j JI ,t I cA a y- . 0 . ( a. I .
0 ut~ a .0 e-s ' a =P4 499_j * ~ SNW 00
4109-9-J 149 IA. I. C3 '. ( 9- --4 ~ ~ t T iwn. -0 -4 me -se -. o .
9-'9fi z &L t &. U ofI *, 4- %Z .. 4 z . ~ a o" I.-- u SN% in %U0 00* TI 10 %I UTX :j v J - r WX -a IJZ 0 1J* 41 41 fi T5J al .7 If 0. "% Tjj NY, *,'J9- .0. ~
vX1 a4 ,4 aZJ '4 Z MM __ _, OL . OZ O ý .
212 I ?ifZ "! 444%1. l T.M.44 'd VI ab VI~S -1 'I -11 '.400. - * et.4 W M- .4.4oUP9f %d a *i 4 .a4 a 2 1~ - 3~h a. 1. v .4. .44
IIIn lz X46 w.3 2 Q E Ms % 0 .4.a =0 ag " ~ r~. -4 of* z 4' A I 1' a4 a - 4 a .a
mcofl4"IAV Ii 41 0 40 0~ X 29 V a .44.0U-32 0 0 v9 w 0 0 . X u. in 0 u. n w .1 Y Y~N aI W. r. re.#ý N t ZZ1&v $U.u.2 4 L,13 t" 50 - 14 TIA
%
.4IN hJ~P .4I%. .ON4 .tn
~~2 4I 4A MM~7,~ * I ~i.~i4..4 tz 0'r U% '00 .I 1J0N.
oac~~~~el in:C(~4I N ~ J9)' ' r ,S *s ' ,
0 U I.~~-~ ~.S J J..)1 C1 u~l. a .l.3,
1uP 2 NL 0C r A WNN4NN .4NN. .
+I
I Iw i i I
ii ~ I
I I
I. 3
*•1 ,rn* I
ItI
4;
• N
• +° __ _ . .. .A
4 r
.4 q4"M lan PS" 4I
Ii 1" 3 aa C
U% I.4100 L3
ISa~ 'CO 0,e =alI
P?"N.4I.P W
C3 .-I2. 0 ,:
CAS W. (AJ
Pt AL r~ 2) it' ''3(-t 2 43 41 4t .4 w.1 L3
.2 * J 4, 111)a zaclCJ.L. IN,ce #iI~ e .
lOP- 0 4 N Z! 0 Q CDPe 'r I- vi 4V1 or v- z S. y I. OY li
E ~ 4 S.S. m w4 I~'4 ~
118
Y SUBJECT: SUBROUTINE WARNING
PURPOSE: SUBROUTINE WARNING identifies the point towhich the warning which follows applies.
METHOD: If no warning message has been written sincethe last printing of an output maLrix, a headingis printed. In any event, the case number,Mach, altitude, and power setting is printed.The calling subprogram will then print theappropriate message.
USAGE: CALL WARNING
Input in COMON
IWARN Error message flag
CASE Case number
ALT Altitude
MACH Mach number
PS Power Setting
Output: STATUS Error flag for case.
1
0 IPA
I~ 4 OA.I I
10 IA I WI
fV -4
lA l * UU &f # s
e Sl ýý-p 0%. Al
0, PIS0On .,
coaw '-
* I
*e N
(1., C
St
Nt0q
'4wtto
Wil
a ai I- ~. U
SUBJECT: SUBROUTINE STORE
PURPOSE: SUBROUTINE STORE moves the results for a single( case to the output matrix.
METHOD: The COMMON block OUTS contains the output forthe case just computed with the individualvariables in exactly the order to be printed.This data is transferred to C0MM4N block 0UTP.
USAGE: CALL STORE (NALT)
NALT - number of cases at currentMach altitude = 10
O 0UTS (45) - output for NALTTH case.
NVAR - number of OUTS locationsbeing used.
Output OUTP (RT,10) Output 'matrix.
1(
S~125
I, 0,0
AJ
*1
men
www
~o "
r2 42 co at C2
C, C3 402 olu
~,.-.-. .- - ~--.----.--~---c
9 ( I 'I I I I
I *9*
I I I, 1
-~ I I I j i
I I I
4 IC
(A 49 I- 0 OA
I l f W I I
a 11 z IA
at IA Iw r--
12
SUBJECT: SUBROUTINE CHKRP
PURPOSE: SUBROUTINE CHKRP calculates the thermodynamicproperties at the throat and the total/staticpressure ratio at the sonic condition.
METHOD: FUNCTION C0FH is called to compute sonicvelocity. Then enthalpy is computed usingthe entry total enthalpy and the sourcevelocity. Critical static temperature andrelative pressure are computed as functionsof enthalpy and fuel-air ratio. Pressure isderived from entry pressure and the relativepressure.
USAGE: CALL CHKRP (PI, Hi, PRI, F0AI, PAM, TC, C, PC,PlOPAM, PIPCC)
P1 Entry total pressurg PSF
Hi Entry total enthalpy, BTU/lbM
PRl Entry relative pressure
F0Al Entry fuel-air ratio
PAM Ambient static pressure, PSF
TC Critical static temperature,degrees R
C Critical sonic velocity ft/sec
PC Critical static pressure, PSF
PlOPAM P1/PAM
PIPCC P1/PC
SUBPROGRAMS: C0FH PR0FH T0FH
128
'7" .-
-
IL
vS I,' ~
z ,
us A , W
o U.
w 0,ILI
00i . it
23!
IL IIo- W, z 64
a. u. IL-Is..' w 4 la) As
di la.1;.jw CL0 Z a 15 CL 12 wu. 1- 11 1a - ZOfAu ~ s. 12.H
AIAN
II Iz I -,I. lcl 1, 0za 44r lý(L (A U.0so0 4aeb-½, 3
I s 4
CO*1
ca IA c
19 f
-'a .,. ca %t
;IV If% ILb. uj 2
0 , Co 0 v .
cz 21, w a.~ 0
IA30
SUBJECT: SUBROUTINE GTHRST
PURPOSE: SUBROUTINE GTHRST computes the performance ofpropulsive nozzles.
METHOD: Outlet conditions are computed, then nozzleideal exit velocity. Nozzle throat staticpressure is compared to ambient pressureto determine which temperature, pressure,and velocity to use in the calculation ofnozzle throat area. Gross thrust is computedby the appropriate equation.
USAGE: CALL GTHRST (XN0ZZ, PRl, P1, Hi, WI, F0Al,PAM, CV, CD, TCS, PCS, VC, H2, T2S, V2, A, FG)
XN0ZZ - 1-0 for convergent-divergent nozzle;
2.0 for convergent nozzle.
P121 Nozzle inlet relative pressure
P1 Nozzle inlet total pressure PSF
Hl Nozzle inlet total enthaipy BTU/LBM
W1 Nozzle inlet mass flow LB/SEC
F0AI Nozzle inlet fuel-air ratio
PAM Ambient static pressure PSF
CV Nozzle velocity coefficient
CD Discharge coefficient
TCS Nozzle throat static temperaturedegrees R
PCS Nozzle throat static pressure PSF
VC Nozzle throat velocity ft/sec
Output H2 Nozzle outlet static enthalpy BT1I/LBM
T2S Nozzle outlet static temperaturedegrees R
131
IOutput (continued)
V2 Nozzle ideal exit velocity ft/sec
A Nczzle throat area ft 2
FG Gross thrust lb
SUBPROGRAMS: AREA H0FPR SQRT
T0FH
132
* PR2 - (PRI)(P~,.b)
T'-
H2 - HOFPR (PR2 . FOA 1 )
T2S - TOFH (H2 . FOA 1)
AF W H1 - H2
H . 0 " 0 14 0 .0 A NA 0 " 0
A > 0.0
Figure-E V 20:FLW.CAR FOR SURUH EGHS
s P33
ARANEA (W1,T2S, Pmd*,Vc A AREA MW, Tcs, PCs, Vc, CD)
•-- - 1.o
Fe WI V2 (CV) W1 wVc fCV)+A (P -P
,. go F0" go "
Figure 20: FLOW CHART"FOR SUBROUTINE GTHRST
133I
op I . I-I -1 0 I - I- II 1 11 1 -. -0 . . 1-0-1 -Wo ewa
I tI00I
I I
j I
IL a, wI-...w~ ~ w w
ow w.4~f'(U0 U. IZ usd AIIu LII .6 L W
J * w 0 wfi( -9 IL III: . 1 10 to
. ~ I ..
CY re w a. I s F
* Co. 0. 1& is 0-0w 0'A U 0 I14 t9164 lo -94l ~ -- II H Q I- .4-1 (
4. 0 OV6 I 50IbZICW4dm ~ N NN IN .91,011 1" C (A .. NCtv 30 5 111,z 0-ZL9w I- WCet-W&' w 1ý G.r£
No o o o a W4o~ 'A0 0. 5 0I mg: )-A (A(A ( C,(aL Nine L) 0-91 1- Z Ill, up w
0N W W Jut- .9 C0 W C
-11 w4 W ILI (A- 0 4'O JZ0"1Q
NI ZO e 4 wA z4 N* Olt ;c z z . i ' lL . .I. IC-'v 4 ow . .2. 1 0-t- 0 01. T -i j :, at N LL 'I.. 44 0 'X
I- -, &IE~1 fl4 e.J'U 6N- tic 0 &NIz thW " I N b i jeaEa . 64 30 w -1Q A(
LUUUqI UI aeNNMWNIW:Z ~ ~ ~ ~ ~ -. 4U C Mm iNN NN INN NNN C .O.~41gl6- y ,C~ 0 a" 0""" 0 ` : 2f(3 tw 7 9.I`J C, . N dg9I'S
IN 3 .. U'
III I-II iI
t iI I I
I j
s I
, 15
's I '
IL I
U.
( f
CJ
N!
I',
* 4
* .
.,L*
N .4
if I I- I ,41C, 10
~ *~ I
000
t L
.4 104 #A II
:0 ca 1C-.
I i L" 92 14.1L0 C3
II u0 * t ca
(hL 11NIJA1.Z , lh0cm 4.
~36
- SUBJECT: SUBROUTINE DATA
PURPOSE: SUBROUTINE DATA provides a card image outputof all data cards input to TEM-333.
METHOD: Data cards are read from TAPE1 (INPUT),written on TAPE5 and OUTPUT. A card countis provided. Upon sensing an end-of-fileof TAPE1, TAPE5 is end-filed and rewound.All subsequent input is from TAPE5. TheINPUT file is equivalent to TAPE1 to providea logical number for the E0F test.
USAGE: CALL DATA
INPUT file must be in desired position whensubroutine is called.
137
- -~~~ -. - - ---------
1444 9. 4 4z2a I me-91144 4at4 4,4 co
Izz l..
w % -
fh.m
w .
* w -. 9m". IIao ae D aW. '- N *# .9..0ý&c 0 N.* ~.4tb
fs 42 Z .46 6
N ZR O.a0 .40, .8 4
N - ORIdP4 ca42 " 0 Zo I~.- *I-
.4w 4 j 01 w- I- .4 N
'1,4 0 uulLJtwm c3wxl.% *0 a,,O
U% a g cm .4.in3 c3 2.s2 caz I ca es~
ty 42 Qt -
.4 .4 .4 tNyw)*ri~f% at0~ 100al
am U-a I~ aýa iGa ' ti $a'1 w a qpO. C) .I.I
I i
I Iy
-m I
to r
-4 1 6 C
2 1 L9 N-.4 fg I
ma us 43 a
4I I
~ 6 Fq 0. N ~ U
-l w ..
SUBJECT: SUBROUTINE PLACIN
PURPOSE: SUBROUTINE PLACIN reads a tabular array. Acount of points is provided for independentvariables.
METHOD: If the number of fields input, NF, is equal tozero, then data is read until the maximumallowable number of cards has been read oruntil a 1 is input in column 72. A field byfield count is made on the last card image sothat the total number of non-blank fields isreturned in NF. If NF is positive, then NFvalues are read. All arrays are formattedten field-seven digit.
USAGE: CALLPLACIN (A(l),NF,NCARD)
A - array to be filled
NF - number of fields to read or if zeroon input, the number of fields read.
NCARD - the maximum number of cards to beread if array is full.
SUBPROGRAM: K0UNT
140
'l C3
"'a 01.4
(A z1-0
of w20
:DA (A
Id D
I . I 4;t 1 L
ty 4 9Of1
06 Z~~.4f 2 ica-, w10
IL I I9 : I 4CL -IIA Ol.
14 ; 40 - .4,44 .4 .
2SZ . 0 0. kt -4 oil Z 6
% tV .11 I" T T N w -1-4 U's g '.a i
;Cz z 39 b 0 i -c 0- .41 02 i .. Ot~ mot. jr
C, 0 64 04 Ll4.AC 0 ~ N.
CJO%. % 2 0 7 9 Of-' j 1 4 - -4't1 Z if . .U. t, L I2 ~ ~ ~ u MCI~t t2 J
~~~C 1* 13 .ft 2I2 I, 4 ~ .
IL 0 '. ?li
IsC Mm . 14 .144 ~ f Na, 14 4-t f l4P.INP.4 ,1 "'13 ''I..1-i .( l..N
f* l L 1 W M . . J C t .2 , 4 J t IIt ic .4,s44 -d Z .3 . .4 ý4 .4 1 -4aCD42* 0 C 2; ~ -'41 C3 4W0t. 40N 1-I0..fb~O . 2
kaI v2 C . 3nesc ,"4 23 ' 'o.
v1 -.3 0 CD 3 t3c 3t a . 3w~ 3 .,Jj0iL 3 .caaC s 9 LL
w m i
hii
aC a a, as0.
I aC a ,
va Ma NO .
CI,
K' .4 IA4C00 a a0! C c
coo 01 0,0 IL
8 IA
N
4NONb 0 t 0 NO 42 AIe12 b4 .4 esC .4 z * V.4 N 0 W
L4 t3L lC a Q -4- 3Q 0 C -
z IACD"SUN VX 0' C1 J QC .0 4 .4.C C,4 2* #2 C2I
,.. t 4 N 0ý N OI
Z' ~ ~ ~ ci Qi 0 C
C, CA0 a. 0. aA
tL4N 1 Aj 5.( 0014J
b-I a~ j 43
SUBJECT: SUBROUTINE TABLi
PURPOSE: SUBROUTINE TABLI inputs tables of the formF = f(x), table format 1.
METHOD: SUBROUTINE PLACIN is called to read and countthe independent array, then recalled to readthe dependent array.
USAGE: CALL TABL1 (T (1), MAX, N)
T - Table to be read
MAX - Maximum number of points in X irray.
Output - N - Actual number of input puintsin X array.
STORAGE: The table T is stored as follows:
Address T(1) (T(2) T (Max) T (Max+l) T(2 Max)
Cont@nt X(1) X (N) F( 1 ) ... F (N)
N MAX
T can be specified in the calling program by
either:
DIMENSION T (2MAX) or C0MM0N/T/ TX(MAX),TY(MAX)
SUBPROGRAMS: PLACIN
4143
1 I2
.44 .t3
IL . I64
I. 0 Igki...fm ca1 3-
ofI
' I'ILI
I.I.
ao
.w CA tj 4 * IL
LA Tm4 z
N lq14 IV 64 v 113P
-a In! Zu: Cal ) IS
1463
SUBJECT: SUBROUTINE TABL2PURPOSE: SUBROUTINE TABL2 inputs tables of the form
F = f(X,Y) -square matrix, table format 2Q.
METHOD: SUBROUTINE PLACIN is called to read and count theY array, then again to read and count the X array.Then for each input Y point PLACIN is called toread NX points of the dependent array.
USAGE: CALL TABLE-2 (T, MAXX, MAXY, NX, NY)
T -- Table to be read
MAXX - Maximum number of points in X array
MAXY - Maximum number of points in Y array
_ _Output NX - Actual number of X array points input
Output NY - Actual number of Y array points input.
STORAGE: The table T is stored as follows:
Address T - - - T(MXX) T - - T(1)(MAXX+)- (MAXX+MAXY)
Content X " - X(NX) Y(1) - - Y(NY)
Address T (MAXX+MAXY+l)- " T(MAXX+MAXY+NX) -T (12MAXX+MAXWI)
Content F - - - F F(1,1) (NX,l) (1,2)
Address T((NY+l) MAXX+MAXY+l) T ((NY+1)MAXX+MAXYtNX) - -
T ((MAXY+1)MAXX+MAXY)
Content F (1i,,Y-) Z-F (NX,NY)
T can be specified in the calling program by
either:
DIENSI0N T(MAXX+MAXY+(MAXX) (MAXY)) or
C0MM0N/T/TX (MAXX) ,TY (MAXY), TF (MAXX, MAXY)
, 146
SUBPROGRAM: PLACIN
//
,, 147
I I
cmI z a I0 " .1"WI
1 4 2
I j C' I o 2I
IC 1 *
IAI
'I.~2 I III
I I ,
t i,
iPsi
c a '
I I
(
tb V
2 a Will aUV 4 c9a A tI'
SUBJECT: SUBROUTINE TABL3
PURPOSE: SUBROUTINE TABLE3 inputs tables of the formF = f(X,Y,Z), table format 3.
METHOD: SUBROUTINE PLACIN is called to read and countthe Z array, the Y array and the X array inturn. Then is recailed to, read a lependentarray corresponding to the X values for thefirst Y and Z; then for the second Y, etc.This Is repeated for each Z value in turn.
USAGE: CALL TABL3 (T, MAXX, MAXY, MAXZ, NX, NY, NZ)
T - - Table to be read
IAXX Maximum number of points in X array
MAXY - Maximum number of points in Y array
MAXZ - Maximum number of points in Z array
Output NX - Actual number of X array poin arput
Output NY - Actual number of Y array points input
Output NZ - Actual number of Z array points input
STORAGE: The table T is stored as follows:
Address T(1) T(MAXX) T(MAXX+1) T (MAXX+MAXY) I
Content X(l) X(NX) Y(i) Y(NY)
Address T (MAXX+MAXY+I) T (MAXX+MAXY+MAXZ) T (MAXX+2MAXY-4AXZ+)i
Content Z(l) Z(NZ) F(1,I,i)
Address T (MAXX+MAXY+MAXZ+NX) - - T (2MAXX+MAXY+MAXZ+I)
Content F(NX,21,1) F(211,1)
NXIMAXX NYSKAXY, NZ-MAXZ
150
T can be specified in the calling program byeither:
DI4EINSI0N T (MAXX+MAXY+MAXZ+ (MAXX) (MAXY) (MIXZ))
or C0MZ0N/T/TX (MAXX) ,TY (MAXY) ,TT. (MAXZ,TF (MAXXIMAXY ,MAXZ)
Note: dependent array stored in natural
FORTRAN order.
SUBPROGRAM: PLACIN
153.
tIL4
X.1IE 43
.4 .4 X )
Z(114 C ;. 2 1q; LS f
10N4:
Will 1 1 .Z x~ 67
z .C3f "tc3 K, i IZIn) N: m a xI "-J l 4J.) 4 i. ..-
b ! L) 3 i
-.3-414 N4444NU4W 1 I ai
J 0i .4z .4 .4aZTZ ~ 4Zt-C J
5 a4 a N ~ a
20.4.4 2 r, ! t r'AA.3no-t 4. .4 .
I ~ ~ ~ ~ ..444..WIS' .4 .
1 .' '1 C 1 L2.1p%
m Z;
I I
*cgs
I i
I II
I~IA
;; a -
A P 4'4 0
to' I W, , -22 0
14
tz 3x 0Iu Ila lyt3~ b. ' w v -4 l. 4A 0.. . 0 h
IV3* IA4 8 ~ -
'4153
SUBJECT: SUBROUTINE TABL22
PURP0SE: SUBROUTINE TABL22 inputs tables of the formF = f(Y,Y) skewed matrix, table format 2K.
METHOD: SUBROUTINE PLACIN is called to read and countthe Y array. Then for each Y value in turn,PLACIN reads and counts and X array and thecorresponding F values. Th% various X arraysneed not have the same number of input points.
USAGE: CALL TABL22 (TMAXY,MAXXNYNX)
T - - Table to be read
MAXY - Ma^imum of points in Y array
MAXX - Maximum of points in X array
Output NY - Actual number of Y array points input
Output NX - Array with actual numbers of X arraypoints input
STORAGE: T(l) T(MAXY) T(MAXY+l) T(MAXY+MAXX)
Y(l) Y(NY) X(1,1) X(NX(l),l)
T (MAXY+MAXXII) - - T (MAXY+ (MAXY) (MAXX) ,i) - -
X(1,2) X(NX(NY),NY)
T (lAXY+ (MAXX) (MAXY)+1 - - T (MAXY+MAXY (2MAXX))
F (1,1) F (NX (NY) ,NY)
T and NX are specified in the calling programby either:
DIMENSION T(MAXY+MAXY(2MAXX)), NX(MAXY)
or C0MM0N/T/TY (MAXY), TX (MAXX,MAXY), TF (MAXX,.MAXY)
Note: X and Y have been reversed in the actualcoding of this routine, but to be consistentwith the write-ups for the other TABLroutines, the outer loop variable iscalled Y in this write-up.
SUBPROGRAM: PLACIN
154
a'9 1 10
t* 3. 2 0.2
* '0,.4 .41-.4 .4 ).
fil )- %~4 " Z . bN ~ ~ V #I~ U 3 b
.J c. V b4I.4 . .4 g. .1 F i dI''# 4i
'C2 4I N r,% r o
%24J aa4. 2 Cx JJ2g 13 M 2(F0 O:2 ,)'d4ZJCV-41J
.3aC . 3'0 '0
I I a g
VI w0. z I Ii
II .0 0.
4( I.t I *
I. 1 aa4
I A*
P. 6- SJ le w'D 0 N
0- 1 3 aCI * I
a. 40 12 4 ý . 2
a 1I6
C, iC. -1 ~~i - 7 -- r00I
00 I00
no.
00,00'
00'
00
001I
nf fln00'00 ft I-I
noI I VI1
0 -0 ( 0 L
n~f rl re~ ~0~I UU '.
-0 f 4 A I.0 o
n00 q CCL.T-N .4 w~ q
00 WNS .
00' 6" L> I a
_ 1 0 -A
00 A- A-L
M~ - ý4II I . I-: -DO JJ 4 A V, 0..xDO~~~~~~I Q. 0 '4) 4 0t. ~
,c'I -. 4 V).0~ ,' -.14D- 0 IioZ 6- 0.1 0. 4k- I
0-I' j I ~..ta *a - "a. 1,s-k- .4p W, -4 .)
M,~ ~V, N N 111 Z- TiZ to C-m £3
0el -1 el'*' . :.a' . .
00' ~ ~ ~ ~ ~ ~ ~ 0 4 % 0 .0'4~0 1 ~ .0 .CA -' -
00~ it ill r51* L) i.L +'- 7 '-;l) .- '~
-O IJ:. 11 3- 1 ~.5' - -~9 - .J I -
I~~l .4 31 o-4 Iii -4.~IA ' *~
u 0L;I U 5'*)1' out ~ . L) 4) 5)t 0. '
I T! .43 n 1 C
c) 0 C2 0 c i 00c
I I I 3157 II
2 � e I
I
I I II .1 Iii I I
f I I I I 3
I i II I II I I I
I I II .�
I I I
I I
I I
I I i )
J I 7
* )C
�
"I I I* If�d4 I I
3a � I
� oa I II I
.� aIeee I.4... ..ErtI.tA. I II I--- I I-" - I I�?.f.1 I I
�;2�?;�I I N
-.� e, I I -..� a
/ � .4N� I
I I
3.p8,
I, -.
j J
Illy
w911-- 1 9
oill at 0. IV
A) S
C` G 044 .- z o U ( .ce of (3S 0 . .
of. ~ I~ (1 a-0C
IA* j
eg 1- 6
10vI 1 woy ~ ~ ~ ~ ftC Lc - AV~f I I'!' x V0j.J
00. 31 i
a 1.
0 d94 2 C
94(L
LLU
w 6fa w 1413M I Iq . . ". I .: *I-0
Z o112 lt 64-4
.44C3 9-0 f* Ps
6N m 00w. mC3~ .2 9 .N N N
F22C, t'9 Cc 00il .J'~i *
•~~c U11 in.. W ..... in r.j J j j j -1
Iwo
'I 1
z I
N IA J 4 IL ,II - t
C iI
USt 10%0 00 1 % A%
0. C. ,42.
{+
j (3 I -. 1
M,- N I
0N (43 MN lo ~J N4
ZI -3. -
I ,,VJ J -,,J
o -1 -o '0,,
%a Co . Z , -
" '44 . . .4 . " JD "" L.j . 3. ,,,
- a,#vw....-m,...4 0 b to I 3 1
t, N N N 0N-6 11% O7O No .1 A0 j L o Z'
1- 0. (A .1- 6-V,ý 50 1 - 1 AI FU .4 4.
on* I-
U 0'. 4 zt .4 '2 .4 Nx
21J PE 'C' ~ -4% 1) - t Ioi
%4 .t9c%4 a tZ . . C-
*L& C0 Li *a.-. % 4
O(M . , f, 4jNN r~ N
n a 0. 0 m ~ .% 9 a...3 aN 3 I c C. Nt C. ' 0 C-)47
To -II
6. w o I -
r *= U- I '
0CA X i at Da 13 0 i
a N ý CCf,' t 4A 0% V% ft 00ANL t
b-1 0 o 1..k fo o
It~~~~~i f:6 71, ' , sI
.4 LL 0 4 4%
V0I U Li4 -4 4 W .FA- U, a Z0) J -U. i J, C 3 N ItCl I x L~r "a I, ICA q I'
4 o m lul 'Z '.4 AN P.,& .. 4
I V ~ .4 L . 4 Y'O .4 .4 .4-4 .4 -. W IA0 14 4Iii'A. ''"nI~ I4 ~ ~ ~ ~ -- 11~' ~) 5U 5 .~ 4 ~ U UZ -~~4
~~~~1 ~~4 n~N ~f i NA~
10 C2 U i ]
&icNj I V-I
IiI
'a.'4a04
a,
II*
0a.4
'a.I."I*
.10
S.4Ii.
*ea .'AN
-aS
5- a.)IA. �CE *a4-ti
* NC.U
ifSA,'
�. 0,* *�
Y.SIll ..4 '*l
.. 4L4�I- 5- Z�
Uk. '� b.�� 1W2� I�.i.j
c�c.4�
�*�) �fl#) .s"�'�a 3 '1*)e�
;I I Vj % a % P
V I.
1 1 11 1)
ma v4 va i 4 4 0*4 4 'y AN WNN N? p 1 f ol m
44 4 4949 44 0 149 W 4 44 4 444 4 4 4F3 ~ (3 cca MOQ n~~ oz000t
*40 V F: ;;cl 44C. C; C
vq4 N A tl NS 01A 61e m 0'K V. '0 f N C ON 0 N
.40 a0 0 N .4 v4 00000.
SO~I 0 "0 0. '4. 1441 "4o 0
to9 N4 M SA N@ f- 00 30 PI V% 'S0 C I.~1 v- 0 0O a0 00 0 0
9.'5, -4 0 Na 04 12~.. N14 "04
N6* 4 N.@ * .31 0. 000 12%0000'M t**4 v4 '4 -50 4 oz P404 - N M 1f% ~N ,%Nt
.*a ~~ ~ ~ d .4 - @ 93~ '
10 0'0 1. -l N .01. .4 t''.00 0D1L1 4'0I 41 1 .4 NN Ml4C N.4 N1ý4
U6 - 6 -0 05 * a0 0 0
N 40 N% .% * 0% 1 *P0 "I 41 IJ'INI*W00 N41.0.N
*0 ago P 0 C .DP 1a'.0 lui 0 )0N
@0 0 oCI o; C; 0 a.4 n C3 to coa s.0 mal oona %' 16 L. M L ag0LM 'A 0
a 0 a0 aO 0000 00. . 4 t340 00. 0 3* t 5 5 a C 0 .a
* 0 .4A~Zl-t 0 4Ni. 414 4o3 .4 CIj I
0 as 00 a* am a0 a 0 ftjN .4 -4.4 4 .4
-.%~ UN 2 00 N % 'q%"4 - *" .4. N 1J4 4" 4 N* 14 .4 .49
-so 1. .2 94m is 4w aeo*a 4
a0 0 It
CU ~ ~ ~ ~ ~ ~ ~ ~ 9 40%e 0 k A- 446 # 04 A kb*64 4-
I i
i7 7
I I
".0 10 N 11 0 N4' 10'"a #W %Cm No 0 11 : • C3 A.-|.t t o , t o % th to tft.UO . to to jD0 'O ' ON N 'CIO:~It 4 .9 4 4 14 EEE 1 -9-944 4 .9 i 44 S .4
00 ,~i~ 0 00 0 = 0 03a ) 11 f z I l1 n 0.QU3 4a M-1 a A4..A-j j
* -•o. .4K 0• •,, • , ,,,
.e ,. • I. .. .0 Iee . .. . .. .. 90 .. e .4 1g9.
4 ;
l~• ++ -4t,0 4 1 Sel,+,, smo •~ @0 U~lN UA.I%.A .I.. Jig+a
... 'F -- 4 . .. . N '9 O.4,+ +4
Na a a
am •. O+to~o, 0 m o m o o o, ,.. 4.4 Ot'. + IE* t'
So n, NO e L•a , •m ma al * ..I • 0 0O . .. . .Co .m fo of a at.. a ,, ma. a-,O
N,4 * ON a '% o 9O~A ftj ~ N Na0 cm C3a a .4 fm .011UH91 ~9 ~ 49amt a . 4% *. nt~ il 0 0 1 a.
J= C;a = 0 C a 0 a N tA a. a J940 cm =M C, go * *4 D N 0 D r1
Nci A n N cu' *0t to a.4kA 14~.00 a 0 S*a a
a.,+,0+ 4 . I,+,'. 10 el I:s a. aai . • I • .4 4 o e, 0 000• +e3
00o :. o . -, :1.,! !,, IPx I MN. I s, R .
00N~g~* MI 0C20~O P' aa a= taaY1 aU o(
a, , = C , , A P3 1 n 7 ' W) "• 0I, '0 011%14 o tl I I•P ;I L
0~ ~ IN.a o
S•4
=42 CN W'~~t. ago04 e a .0 0 m 155j00A00000'. 0 ~ ~ .*o ' U% UN IOntA 5S ~ .4T4 C: 000 5-u UN%0 04,
M I~ft y 04M.4 1.4 -A 0 0N .4 N I" -A C
Uaa~~" -49a a3 coc LN cm a t S-I. ZO a 4- a5~ O 1
~~u ~ oaaano : a- aAf ON C310 0 0 Ma~ a~ 'Nj
no0 0 0 14
0 in C `%N
SISCTION III
DESCRIPTION Or FUNCTIONS,.AND LISTINGS
SUBJECT: FUNCTION AREA
PURPOSE: FUNCTION AREA computes flow area
METHOD: AREA RW T - sq. ft.PVD
USAGE: A = AREA (W, T, P, V, CD)
W Inlet mass flow lb/sec
T Nozzle throat static temperaturedegrees R
P Nozzle throat static pressure lb/ft 2
V Nozzle throat velocity ft/sec
CD %ischarge coefficient = 1.0
167
I A- tI !I
I I
)
* .1
.,0
*I .l
*N!
t ,.0
Q I' lI 'g f
1 °
Si &
I °
... I.
W9f
SUBJECT: - Thermodynamic function set; H0FT, T0FH, PR0FH,C0FH, and COFHS.
PURPOSE: The thermodynamic function set produces datafrom Keenan and Kaye Gas Tables to the program.
METHOD: A polynomial fit of the tabular data is used.The appropriate coefficients are detirminedby the checking the range of the input variables.
USAGE: H - HOFT (T,F0A)
T = T0FH (H,F0A)
PR a PR0FH(H,FOA)
H = H0FPR(PR,F0A)
C - COFH(HTFOA)
C = COFHS (HS,FOA)H Enthalpy BTU/lb T temperature degrees R
F0A fuel/air ratio PR relativepressure
C sonic velocity ft/sec HT total enthalpy BTU/lb3
HS static enthalpy BTU/Io
The fuel is assumed to be a hydrocarbon ofcomposition, CN HN 2 N.
)
I * ' I
0 Z
C'4
e. 41b "4 "
* e
(I -
1..1 a a N u
~INI
0 91 O t ': ' ý s au- 1
Sh,, V
ne is• C'W , ,,1. 12 6.wia ot a w W a ,,l 0T"06-Z " c Tl,-u
I IeaIa I)
,A ca I ,, Q 0 0 00 0 u0, u-W-,-iSi 4 ,+'17
fIa , I *I 'A L .elmS •
.. p . . . .. ..aJ~U n . .IN O.S.•40 .O' , N I(~ .4, IZ
,+ .l • .UII+ +,1 q " ap'. p. 'ua
I I I - I l ,' * 0
a ov
PA I I
9, I
me .
I ..
14.e
t1ame 1
t. ] i ,
I: 'SI ~ h 172
-4 4.1 ' mii a 0 ':
I. I I~ . I '
I I ii
P. fl
as 't
46
I 4 -I % 04 cy0 Y0 1
*1 #* ~ 1 - v ~
Sm ! a1 0.:i-
4 -
404x 1.0 IV N N %S..
0 0 *@ 11 1 41AI :
al4~ M. J P.
fol 0-4S. P.6S lb. f- a
*OIN N '. i I% I
u W I 5 0. P. N 64fI~d Oki, a IL4..h
64.
w0 Il 1- 1.040 . 4 ao f -
40fobI l s~lUL 6 JI~I lIe u ' a wwo
IV
2 a Is1. 1. 4-2
41 1. a j 0
30 m I I)
5174
Fil Iw 0 I
"" 4 "O
I' 1 ll ft II- ;P:
I I" I.X I 1
CM no I ita C 4UI.I (t#
a PCAt f% If
OWJq f- 1 4 -R ca ( '@N .4 ly(
64- 1, "!~ Pe4 . NN ..4
RI~~ A~9 ; N*fOI..A *aP.
2~ aV 944
J~~~ .3 1A 440AI 4 0N, 64.10)
C3W 6 0 I n if It 11151U%. r3 0r N If% 4 i. .
31 1. 75 . i
I ItI. I
I II
i )
I-
NJ
!J IA V n 1.
~~~~~ it • "••1
. I .... ,
5 4 1"k
v 0f
0 it
~I .76
---*moo '
190 ' III
9, a'J 04N
.4 MR M4 M9 . aotIi"IA~~~ tIz*MIn. "
q4 IN9,4 T ;!j I V4 % Ca, 7*9tek 49 o.' . y
04. 4 44 4kP 94 of WINS 94 34tM *W I9I.In %aI
aA9 *I0*.~@ 0 @Pt1
R~~ tI w w ~f$ 4.
b. b.p 9 0 ,96 64 00.J4N V al~* s~94Otyea t 64a: In. .4 0,0N I
04 00 Iy I%, U% .
In* 00 .4 . V .3%*9
I I N
-~I S*I .4 .ft .41 .4 SW anj, Ia. N* 0% In~ %0 14 to,) Ol of ta Il I%"* l l*l a 10W N- . " * I a, It ";* IrE~
#A 015 *4 IV t:6.0*%I . mOf% *h lo IW11 *",I*5 Ir. rjif "4 aa ~*d@t9 .1.4 0 ~ ' Nil
4~ ~ ~ ~ ~ ..14 .34 Na an 94n .4 INN # t99 1S.J *M.4 5,4 m
Sol 04 1;;l 0. 1 COMAJ4.4*A OJbDots4N*.J*I OON m .PISNC l .4A A')
OR. 20.1 1. w .j 110- 44 O 0 4i 04 1 Va CI O Vs W a1-3 s0
..1i77'
IOU
I
;
WN i ILk
%p Z
" o at c.
44ac *4
"I ID IS$ 40 0 L i
Uý V4 0 1.*
1 .4b. :4 Xt..i .s IN 4b N i4.
49
.44c t o - I.4 S
* ~~~ b4..0 zta U. z 6 1 *
~v,.J. *4t'4 S
.teIW t *A*
eNIO * Nsa4@4 17f
foo
I I tooI I j
! fo o? a0-0 e, z .4-6
14 9
mem 11m0 , awmmi - Aot
I 1J9
*t P- co o. - -- - -
v IDNMIry, nI In InI
4r ty--1-el, -P 0 N nS
49 I 0; *A I" I I (
IC, D C3 0* t~ N (P It N m "I .3
P.. t3 IC - 1 1 1 i . . M ~
W 3
jJ Ju i'. 0 .n041 Ný 3% C
6.~~~ ILI -4 1" 1 0
4, 40* -4 (9 1 P. f N 1 . *. 1%1 fi * . b . 4~
04N M '.. N 4 age .4 fy )4 .4 Ij N 10 ~ C3~~ h. OM I * C S0 *.0.4'j .%6.j0 IA6 3 (
4 4
4U)jJ3 4L Z V14 'M
l o D 10 j3 0 1og J 0414 ;i CI .4 . It .4 W )
", 6.. 3 4 -0% " N "', - 0(" , " t
sm ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ 1 6.%10 y i t44' . -. IOg~~~~~I, am " yf % tMM
IL.
41 4
4 b4
r 4
C; *.ý 41 .41 ~ Z 2 U%4
- - 4.
U. neC
f I Aj I
3 C,
¶ I
8 T
C3 a!
gmaC* I o
0-1 s 'Z b.liNz
A9jo
2s ts P;.4C.4 (A ,L,4 dl L 3 (
a4 9 14 Zi A 3C 4
21' .9. w1 1* 0 1'loN I WE E t E;E
Ml04~IJ 91. -
0-O r.L ý4 M ~ l. f~
i u 'P. id I V-
04 N N IrJ %lDL7C nd
u , 3P._
6-4%DCll92V-Lh 0 ~~ " %MD 49.4 VP t4 t.,0...D11% t* * g0 ; 0 U-.4"OI *3C _0
N " i% 4 If% N .4 1 1 nsnF"J 3 P,.*
9 0In t0 ly 1:3 CI 10 onC amI-n.4. jU q I 4 U% -3 IF. 0 ;' i N PI.-4 .4N . MF.M7I 0 .4 IDn CINMIo rNI 0
0.. 2 L y yle 10.4 ' o III I aO 0 A11 .4MN .4 , U n 1, 1 .4
or z . 1.4 .0 - OU% 170 U aY1 .tP4 ~ 4N4 N 4.4 2 0 In inN. .L.4 21 w0 *n S~* . .N 0 .44 .4 In40'~ in".
44 ~ ~ ~ ~ i inD~4O.- '1- I.. 0 1.0. .. tmAC~4~Z '0 .OIJ.V.4 .4 N fN M 0: .4 1 1 14 1
49 0 I *Sl.4N ll 3.J 4 ~ -1 3 N J nl Im f..gg1 0*% 4% 14 1 A"'0 1 ,. I 0ýIIMIl(JN
-9 OrN . tA .0 . .II 0. .
ae 1.4 ~N *.4 IA0 .4 * N .' .4 IIqIn0'4 * .4 N ~ *OAM.I., " %'1 . (WY). I I. f.. .4 t.a , I. . % ~ 0.44 1 tl* r~ IlP
oft 111 4A .44 *MNM4 CD OnO ~N .4 ...20 ..a 4 i. ~ )j I N N Ow 1, 0 4 a 10 a1NN 4 MIJA4)I 4 D0 I
tiI 4L [A~4 11,3 4. 4N'S4M 10g F% 1 Nt0 N
Z II 7% aaI
1, 5j NIJ Nj 4A cp JA 331DIN N NP
(A Il) 0i -94 x " M r 'A .4 N ' a3 Ma NO4 0 400 I t ) P, P_ ' 0 .t iis j oe. o . In a " 0r10 71 1 a Na )a .LA t,~C r *ICIt t ý .2(A P4 I -a* '0I'D.4M C11 " -dN0j 1% (- 4 1 34 t2.4 "
1'' II~I "',I
(a IW 7 4%)11tUt l 1.4 IAN 111 1 .4 ., IA,. 0re 4 ,fJ,.0N. 1 0 I¶IIIII I; MIS 6NN x0
* *g. 9N
CIlM4~ pq~
*11 24 '" IC I a. NO * .N . . r . 1-1 ;7j
.j wN w1. ( In' 0DP on' K 0M.4''N v J tfJ%. ~44 *C3 I .4-0 F... C3 -D1- j. P4 cr 0% .1 N.1 01t4
N t --
I NJ -'2 ' " ""1 0. I .4tI%1 11; "I -* A -. A I r .4-
ZI 1I N Ir J% '' A.4I
II ZIA, I. III z k IIA. , 3 .S.
C3 a Q Ic XT I4 4 - 1Z UV
4 i CDI i
W L IV L
4. .41
atF caii F2 C ,C
I I IAgo2
I In
IA 1
.4fu1
z II Inw z(
Id~Z 43 C bI A*i
* In
IL II 4 Ia4 IV
Ij le I v
U) i 41 C0 6y-4 ce 4 ae L'S I-4 f.2 0J.1- S- 0 V
U" WI Z 1-4w V
2J5 41 j555 .. - L
75-1
SUBJECT: FUNCTION K0UNT
PURPOSE: FUNCTION K0UNT counts the number of inputpoints on a ten field seven digit inputcard.
METHOD: Starting with the right most fieli a testis made for a blank field. Upon ..indinga non-blank field that field number isreturned as the input count.
USAGE; K = K0UNT (CARD, NFI)
CARD - Array of input points
NFI - Maximum fields defined on card-10
)
186
I. II0 I
IL14
IL 0
.- w 1-
N oIN
0 0. *4 0 ( ,
0' 2 - 4;0 045
ly (A ta 0 -9 ? ~-j* w 04 3oI of J CD sI, 2 tv w .4 t '~g.V VIV
W I
o4 Z da " -4 *4 to -Z
CJ3V-'40 I.)
0 49 T b ofUILb-10 0 il2
w z x le187
I I
4 2!
CII w
s qrW z V
V) 41 I2 w t
0 O0
af W IA
SUBJECT: FUNCTION DEMAND
PURPOSE: FUNCTION DEMAND computes engine demand, Ao/Act
as a function of recovery factor.
METHOD: DEMAND = Area RFWC + Area RFW + ABY
AC AC Ac
where AOBY is from Table 7
AC
USAGE: A0AC = rvMAND(RP)
RF is recovery factor
Area = AREAF (Mach)
WC = Engine airflow
W S •Secondary airflow
AC = Capture area
SUBPROGRAMS: TABU2
18
189
I I
cm I aw of
41210-O N O
fbi 4W.0 I 9
' a a a
on on Iq 4 ,4ktI
.3 IsI aq 1 1.ex C, L ab IlItoa oI" %
w2 a- -. 0 3
o- eta
.40
InK I 'wco caU
ty Li09' C
C. 0.4
Ip C% 93
ra ft 0
oX1
O. I
I.I
v!4-
in
1'
-W ., T O .W
i* 4K .1
K
'-
15.61
tja
;In -Ses f '.a C , -oC
" D 3 2I,
63 43 aC3 ca EK
* 44 i92
-Fri
101
i ,t
I I - 'I .
W, 4A
o III ' I t
I .1
tA o. . -IA .
j Is I
$ It
i Io I
L2 b-3 I I jI41193
I I
I I I
I
I I
Ii
III, I
II
* . .. , I
* I, S. I.Z4 I
* g 1•s I
* ..I II,,, a
41 4
I II
,I 1 i• 114 %1.,! I .
F"J . - rlll, r 1- •
ei t
bD 0 Dn
W1 IA
13 0 - 03
.. *Z 311 4m
w I %
9z
w 0.4
'a 4 "
ev Ih 5- ot ! f2 O 4 I5 4w ow l m e 4 1 ~ 1
6_ 0. 0 b. C2 . . a0~ LP Ai 4J 4A '3A L
~" A.J' ~ 195
SECTION IV4
CROSS-LISTING FOR PROGRAM TEM-333
196
r *
Z .4
(0 (A 1 I I0w 00 0 n c
I.-J oil r". CA 11ov ~ ~ ~ .). -q1. 1 -4 -
I
'A. sAC (ALI P v0 .4%
J4. 1. W(a.W
.00 0 1 3 5 y
I- rr - y
0 0. I L) o
ii
I Id 4
I IF If %. 41 4 .
CY AD.N N e4 N N
ruN AD N IN N3C
U) jc v 03-
4.4N, ,.. ey .4 ~ IV .4 If% .4 -4 .CY fu N0 4y ID N
IaJ--4 VE .14-4 ~ .I
It.N. z d..4 z44 . .4j.. V. 13 fu -1
.4 .4N Nl 4 a D y. 4 I %4. N N .4 N4 .4 .4 [4N N. .4 cm4 l
A J .4 -440 C3 .% P. .4 th qr -30
!J~~ l t.I % .4 1 ý4 NN o 7I
A j0 4J'0' *J3 0 4 K444 z4 1-44 0V 4 4r 1- M o. Mi
'4. NfjP..4 '4.4 ..4 ILU 1. 044N. .44.. 'gI r it .4i M 44,nN 04 N n' NN Nl n-x I `
4. .4)I axu 0uI-X wPL t I N-
.4 '~..3 4L fi I/I e ''T -A 31
'044 .9 .8' -'11
of 4 - -
P4 a L I.-g :1 0 IA I. m
.4-4
P)I
(4 M re InI2 4 4y 2 . .
*14 49 .9 0.9-.
^, N 'my N
4 0 4& 42
-Ina T*
04.
LL w . m,sr -'N .4. N 9 .' NwXI (.3 I
1 m X$- - p I.-4U'Sd. .4 .
0. I~ 4- .1 I ( -1 t .1 14 10 1 4 M 4
j .111J64 u4. h4 ~ '.1% ). a
MON""!'~PYN
it~ '~, * le
I * All
I I
a of a. '
In a
w. *8 000 .06 .0
I U IVK a' 19 ' Va 06,4 10 a P4 Q
#5f OM3 we I 0. *a 4 04 1 49 a
go dc = h. 0.' 22 4421
of At et j wJ 41 4 -j 4J r"E % I II te a 2
a. UJ # us VIA ILI w w1 Al " I us 'i""0 "11
ac W' ft 4 x146 Wb w' U.V. t . &
~ o) 1* Oi 'ii Iii III 000 ai *II W1) I '.
N y Nf , 1 N N0 5 * y 4~
7 " I a 1
.4 J -
L4 V a .
654 lie if,2 2
.4~. .KK K4 0. 'I 200
I- I
UJI
11K Id
IWO IS IS
4 0;( 11 ae
h5~~ c- r2IT2 0. 0 11 IL LCIo (
In 4A In I ( A V
III IL d .1 o
to Id
fit I d wIl
IL U. w. w le U.w -. a
09 Cie ty af Of of af ar 0. at t
IV IC N, .4 Qy 40 04. y A N
I- I -0
KIL
T 43 "5 2 (9a
~a V Id 4 r III . 1 4.11 J 5 I Ij i
IN 49 It 0s ez a..
I101
- I
I *I I
. , I1 . I
I )
'.9It I Il i
tot.41 Jn
II
Q V1 0(At
I I r
zW of a N t !
0 ,.II II
,•) I I
'I It mI m o 1 0
', d I, I.1* 6 ri 1I l 4 6 •, a • 6
" 0. 0. , , 1
It i I I )
9*9IN
0 IA IIA 0II N IA # A 0 AS
'4 j 14 1 fil I'j w 2J 2 IL 2d 2w11 ~~) 9*9 I~ 4 3 4j. U, 4' ' 4 ' 4 4 .
41 111 111 us Wa its Ito ta liJ 14
at Ul Wa aI '*9 at C
I.,J 's 0 0 43'U U f U 0 U '
'. .1 1 Ills ILI - 1, 'if is Is 19'i ul: . * .I 'J' Id9 ILI 411
2z IX 13 ~ X 2 I X X E 2 2 2 I
f39 ~ i I'm 5vI 2 ,i 0. 4 -
;f I I- 0N .i' ' ' 'l ' I '
rx I ~~-.1201 gl
, -!
I,: I $
I ,
I iI I . *
* I I
1 I ' I '"
,I' 'I 'Ii'I * I
:.... i
SECTION V
INLET MAP PROGRAM
204
SW SALve ooo;oooCoCocoo2oooooo00000OOOOOOOOO302OO30~30OO)OOOOOO3OCCOQCOOO03cooQocoooooS116.6V 000,.. OOOG OOOUDO300000000JOOOGOOOOOOCOOJ33OC O3UO00 000000JC COO OCo)UU 0 000 CrOOOCOO
COOC1.33 )ATA IN91AJU4O/IN.oU
OOGO33COtl-lJh/AR-jAVL/ARTA
CCQ 0J C.13 i/NIA.4i/ X Hi.lN5
@00C23 4Otq.43h/OJTPI'L/OUT*1NL(;) ,C3,OUTINItI.
OCOG33 COP.sijN/TAiJ.1 /7132440*0 TA92AY14l~j,?,A
000033 GOt4i)/TAaZ3/TA32~xT~(~N
OOCO*23a JTA;X(;)T82ytlIN2
20063 3 JXMP-ws14SO4 TI LL (:3) LAJL (2)
A, OJT7(14)4000033 -OHN S 10 r'iACH(33)
0004~3 JATA 1/1ICOGJo JA A 7EL9.3,1'$ Gooo
iouuu 'J.) JAiA CoL~o6E.4l .n C, / 1
000212 WdRIT; Ab,833 TITLE* 003C2p. N T tO.A.0HxJ__ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ _ _ _ _
OC3&2 sKIZ 9 01809302 CALL PLAClN(TIACI,,IIMACN,3)0 0 0C3 c READ(5,b) WCLfjELedcfwCU _______
6 ;0 .4 2ARLUC(69dwZ) WCL#.DELwiCtoCU400654 CALL TAUI.4
-9001Uý- 3YAAý-Jj G/ C60005? IF (3ELwk;) 23#10t.20000360 LO0 W4Gu1La 0c 6 (1 4_O T3 30
62~o 20 *44CLFIAt(WU-keCL-.1)/tELW,)4,2* cjc-?0 3) JuD
ccgG?1 NwCclINC(Aofh40,.)____
C03:76 ~ jxjfl
CGJ3J3 Jo Z;; K'lp4WC_______CALL 14~XiC, 7 ~3, 1 F
OCOLC IF(1.1.11) OUTv(,K):eC*JYAC
00C321 OiiTI; J9412CO ____________________
205
RU.' VERSION JUL 7?1 11*19*li. 72/36/29a
033tic NT2A=-NZ._______ON 12 ~ I -17VT J-iEfiuMACH1S) ZCS 220 ;M20
UGO±34 2:5 IF (XMZZiJ*;EoXIHIN) GO ro 210AC3137 #lCACUL=ASrE-_603 14d :'Li.-.AST S
UG11COO)L= ASTEA2CCOL4'2 WCALU3ZzAStEA _________________
g0a±143 itF Uz AST --.OC3144COOls AST9II
000145 GO TO i~ -(TB~YA'N2c 43 Ft 213 A;G~T6lXZ:OTa-
403152 RFOLzT81U(.AiCO&,UTA32A.~,TA82AYtj~NT2A)Qc31*b WCACjLzA'.C3L/(AREA*RFOL) -
00316%2 CALL LtNLOD&i(XMACNP,WC ,3.0,30G,RFOL)C03166 C0CLzlCO _______________________
G00177 ENC3OEt1;,9'.29WCACDL! WCACOL0%03237 ENCO)t(139931tCO&)L) COOL_________________
4G:22L. IF (AZAC3ZL.Lrc..;) GJ TO 215C03225 -tF6~zTeLJL (A3AC3Z, TAO2AX ,T482AY ,1,WtZAI
G~ -.az-O0~234 11=6000235 5 90 WCxW3ACdZ*#________________
c~3e IF W;S(F)sLr*Zs..;:5) ;j,, TO b _________
a ~ic Ii.F l7FG~) GO --;- TO --b _______
OCC254 IF (I4.)GO T-0 61i
00:237 613 IF CF*E3.*FSAV') GID TO 64.00002b1 XXNA3-WAS-4E:*/FFAEQC3267 IF c4XoLT*G*5) XA3:%5
COC275 FSAV-*FGý077 C.~t,;3ZzP
0301 0 T3 590~
004332 ;ZFJZz-Co3
OCC313 COU~z-Cal0C335 CJL=CD
GCC333? ENCU~loa,'p9!9F'3Z) PFDZ _____________
OC0 1.6 PwCA i043326 NCf(.,1.CU)coJazcc:3 3E GO TO 23-4___
00334.1 R F d 1=ASTGG9323i Cud Z =A ST cE.1 ___ ________ ____
20,6
vU VERS O04 JUL ?I ±IsS ?ll3ef2;o
0033.3 OT3 233UC 33 3 2 A.IACJLxT.1..U1(AfqZ:-JOtTj 2A8ZSA!.;5CljojN!29)
230350 ttFP;La 1bLt~tLZE*OIADliATA3i3YLP4TZOI* coassu. biCACOLs(1. 32*ACA..OLS/(AREAOftFDLI
OGGSS7 inCs.IQAC0L*AC________________44~0361 CALL INLjv(~A4CMACI4pPqWC 9)g3i*09RGoFELTGC036SG5 ~~IC3367 9E-ENC0hJtj#:Iqstvol RFOL463C376 ENOit.#o;9GwO WCACOL
64446 -NC30E~l1i39;l9COOLI COOL
*000421 C081SASTH46100.22 -2 U. OUT ItjIJaNC ___________________
060426 QUT3lJ~atFOL
904%31 OU17 tj)a~tjz
00:434.O~l~~36GO435 F((J.LT.1:).ANO~i( to.T.NT4A .4)) GO TO 330
C OUIPJT RiCOVER1 HAPOC044.5 LAeL(l)aI'4IlNLET R-NO
* 6044. LAl3L(Zlxl44dERY ;IAPsc;4Sc WRIT 7(tt 4; 3 LAt3L't T TLE IXMAC"St,."C163463 WRITL"b 1,461 OTil ABl.L __________
1 00511 wRI(.;tb,3Go (0Uf4(L),LCItJlC058 jRTij4.'j3.lj c"T~n(0L=& L2,)OM~3 IT WIHlbo~ioi COJT'/(L) 9LaLJCooSS2 11RTc t,930 (PLAdLEPL8IJ)_056_0 24.C Kxjl&c;566 uG'Utc6,1313 OUT%(K),(0UT3(LIOLx1,J)000634 24) CONTINUE
c OUIP~JM 44-APcca63,Ay L*AE641zlANL4f OIAG4 00616 LA0iL(2lx1;4 MAP
601 lft_____I LA*lLT1~.jL!4q $ kA JAC________* c36?5 witIT-* I b3.'.) (LJUTl(LltLUJP
CC3053 aiRITE(Ft9LI) (OUrTAbL) IJ
GG372b00 25 019NE966?30 WRIT-'(69)131 OUT'e(K),(OJTlJ(LK)vLxaiJ)
07 6 250 -G-ONTitLN E ______________________________
gCw?i2 3-. CCKTLNUE063755 STOP ___ __ __
CUM7 8;1 FCRAiATt~lAA',HN th.10:R ARRAY*)0C66'412 FORAAT(#:COiR-CTr-* AIPFLOO POZITif I'( 7i1I~ITIALjl2X Se1ODLTA, 124
I,0
A34FI,4AL /ZSX93FPl?'l Jr S $1 F OR"H414 1 OF7 ?___o______1
U~~27? M2 FOr?4AT tiA13.) ____
cOcO?3 9CI F UNA T~i4c (FIK,1 F1to)
OCC?7 );i3 FORtIAT(1.CIS-tT~oodq~~tlcn ?A H.G9SJ~xl'CP E Ak______
O&C737 9j4 FOR,447(SLtBUZ 44CIH 4tIZX,1C4(CCACILx121
SC2r?5 90 FORMT It1EF112,6K,1FC.4- IM )19;(WCAILXýA1op~a7s7 911? FORMA T EIO C UZ IMIT / X 91UAO ___(W_____ACI_4_t_?____13_AtC
fACGI5? 912 FO-A 5s64GU L)9IA0OCO?57ENO
-- - - -- - =
IL
(
g
4
(I. *�
S.
I-.-a
IL. W�uo a
TI-.
S..
-he'*4 04.0-.L'*-12
0 14
C, �4I., *�L1.�"'14
. a.�. z.� 0� -J
4 iv144
tLI tIj� �
!Ll ; 0 V
I~I IL I 9I S
is 0 .4 .4fl w C 4y P o --. g
Wm ci W% CtW , " "C pC jc ,r ,4j C
1 0- tif 0 9 1 0 . o
Pj .e .1 .1 -7 C2 CA cl vsd Z.e ElI PS' * *1 1. Il
CA alC, " CAC rj c, e. C., 440 cV CAI cm 196) 'rb~' ast Cft
4.91 9C r A w CI 4., a-Lw to " "iLI go CA Li
4(C3 go c% C. ja & C AI go ( CC CAc Up %;,W go CA 6. 2 a. C .' C. ILi LI C: . . 4 i LI CI 9.:. -CA LI
- ot - Pc pc l. 9j ft** * c- CA C3 4 . l c. 40 C2** .j P . , 4.
42 Cie ,, = 42 El? c- " i CA c, cil C2 'Ir O c .9 Ci A 2 4, 92 g C S C A C % C3 =i cis c- to r, PCA W1 5
. . .C 4 .I6, is . . . e: p C mc : egoo - cg. 4 :- c -,i .t~aJ Lit*L: c:cp W1 CJdoo (.9m4 & 943, Ca if CA C.9 £p P5 6 go mc C0a cm to C~ ep 4; 4. ;111c C2 w 43 (.1 LI4i C.,
]e np' C-1 lO-0 Or to SO e C 4D 9 GP1VC latA6JCOA
., ,~ OfI 0g
CA cICC l ICC£ i o onL D I CC 41 CD Orp 02 LI 2AMe ISI 11M VI I C AI CAL 9_# at CIO CI go(dC wIID3DIJ).Lt i ~ C L I lliiLt L ILLLC I L
(D L C 446. I~iici C I I so 4p f.3 C* ca 4 C2 14.1 lip Us *4 LI LI i La LI 'p LI
~~"~~' 0 . .46 3 A, .3 .9 0 .D( ~ Lii3LL A, L
CLI-. CIO4LIIILI3~ co to 4:5 CSI ills CIO
CC ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ 1 C.U up V14 LI 4.1C Qp. Ci L 3C C II tlCiL iL I L I 'C I L
(3 C 143L % IA do us A iiL 3 C , 4 i QU a£ Ib L W. up C.P . P. I. 3L II I LCID o% I.4 00'P.P t .NO 14 . v 01 CICo L4 I. IsP CD "914 gC CL I EE
P. WA A~.fI. 4~ . 01 C3 04 C I 4 .0 wIll CP Cs C 43 g.4 CIDU r3~ i.
41.2 0p SO A, COP U S Oil1 C I L
C IA ( 5 0 4 t t 4 3 4 C 4 3 4 9 E Cs L i
%.1 0 4 .g oL I I £ L C L I )C C C I F
9-V( 6p 421 A9 £406 I. 6.0 444 93 P LI a. 4.0 4.0. GA4 1. Its cit: 64.4 p 6.1 '. C2 C2 CO 4 4 j C
cii LCP5 ~ i.Iq,* CO l I V,~ EicmCti4 l `,c IC ~ CA
641 C, PtV . 4.01,1 46! %JV U%436
460 A *0 AM ;I -. * .7 .0 M. c . . .
4j "T :: " r'mcm LI Cs EDiICII C~6 c- r9 CLI CC CO2I CA 1.0~ r CAc PC3 120
Cci-oAWI1 ItsI 42 Cic 41 992P i CI coc eCI C '. CP ft WI 41 c C
In CA I .. .. ~ .0 P.0.0 14 VA 0b 40 CD Wll v-4 LI Pp ;o CF C ICP "7.-a . 53 4-*4
IAAL do P.b 06 ' Ol.'11 P.O 4p ow . I P.1 4 dP B_.4L JLI. C. II. i
lii 0, n~ is tv e.o.
ID ci..
W. L0. p 4 .. .P
%J Is go 13 g.9
6 2 4 goC P . 2 z D 0" 4 11 C" % Pl SD.0 4D * . :o. C 1o,. On V3 L
"I*p & -9 WI.110P. P. Is pal SGO: PIA. tA.,. -2 " URVII W% in ~ * C -0 91 " IrAM `-
PA 0% SI~I 0L K 0. 00d i 0 0 Al-1 U 0<
r9 ci a " %js -.0. up 0.11 us It Ait Li a. aJ% CIO "4.
%A CD% P. N. PAPS dII LI, 4. r 1 3ii. . dA
a-... Ib *[email protected] * .r p I0 '. P VIl yOt
0~*fl~ 01. ',0 . f0 P t0 . As Al .~ Op A,
31 -D39 Is3 'a 4I C vs SO m Cp .31 ass op 41 ii qt,rpt 51,4 fII.3-,* -n 3#7 1
10 CA 4 %pt98ie %p %9 .4 j* %&V C-iv %, 4,19.0. i "~ a1 GA3 &#.. PL4%
A .4 old% A iP PAf. ft .30 OP a. 0 63 1 4oir ! P 'f 9%".1 [
41"~ 0 , .4 ~ 0 0 AviiIPLC L
"" .n %.%- 4V Pi% *,
1L N-= c W o 7;
X*r '5 .0r0 T. £2 10 dV.$w o - "l 1 .435-21,. 9 r,Li ,.. *11' ~110
4 4
gar C".l a C ,c
aa V~ OCl CP a al 42
C92 S Ooot) C 0 CS43 2 lpC
Cii Ow C'001 C01 0 cp 0 ap "" a co l0
4:C; 00 OlO 0 0'
r~~gs3 COso. O 01)C
* l 0 5 000 0 09 a IOtw
00 .~fDO )C, 0 r,00l W. C%"3 La0
02 0 W r4CbCA
ot C2 9, V4 00-100 t3003 a jC 00i
C: C;00 c C; C;
' 40 a *@ C 2 "
C3 es cii I j Ia Im m00
C3 03 a1 O 0
00 C 0 tO'cal vi0 00j *L3
L, .) 43 co ev QI -. @ 3 0*63 = UC i)00 . 30C
*0 P3 0.0 c C 3cm L03 OJ14o
00 00 44I*r
.I. C;
C, ~ 3 ~ *0 C3 43 'a % JO-C26J %30 0 % -1 400 .3 u C3
C30 1 .4 N s,
C2C
U) @0 (2. 3"
0 a - C -, * :1,ý11
"1, 01.. ' 061atvat0p6 oa- 0 c 4 11 0 4 4
a. m ,t o '.U ,U Aini %U %U num
43 b 0 .. ono nnM0 %%* *S 01000 0 000. o0O~*00 0 4 00 @04040a041
£ 0 "10 94 " I
C, INIl4: 0 t .4 N a a n~ a @ m v 0 l 0100j 00aIIIIV t9 Ill P at N (V -NN N N F.N . P N 4IN N N N ON .N iS M N t. 5. N N N i '0
w P)0 fy0 ee NO00a of... * 0 .000g@ @6 0010 90 *66
I I
IL U% C* 4 am I% I) T.44".
IN 4m I*M 111 0 % 43 a -4~~1-4 * 04N m*q4. 8 MI .4 0 N 4 Im -7 I's
a.jC
I; C; 4'0 '00 0 4DI NNN NN%00%Dl %D 1A O 0 ONM V% ty M
W4 O Ne No. @V0O* 0 0 N 0 0. N 0 1.940IL *V4 0n.f...I A ~ .. tN6 O9
0Y0 14:4494 Ole 1 * 0 6 1 * $ e o
01a . ft LA el,".a& y.,% t"p-0 f p11 3 -
P. 1 4, & C* .3 ') %0 %a %V*I .Nt 13t
~~L4 **
0 1'* 0
0 0 0 6 0 060 * 6 0 6
*1 % i aa *4%(*6% f1 nf~m10 m
fm 0 0 0 0 e-p 0 0 0 0 0 0 0 0 a 0 0 0 0 0 .N1.N
ceP3- 4 L3 111rfMN- dmn 1':k.DU 9 iN #1 V%1 Pj
jo0 1--212. 000000000Ol
CA -lm C' CA a"
Z a -sIOate oC I %C o Mr %f0V0t0(. S W c
gsgU 0 *, 0 6. * 0 &o~o 0aa 0g. 430 0 csuuc0uoa
10 92 CD a a a. ev 4f0e
49 *j *j a * CD Li ai L 4~.p)ip C7La j Ai r ti C A~ 42iL - CA %j %j Wi f: fLi L3 CA c% CI V t q to LiLI0 " 4p p to" 4: " wcofJ0CC)C
a 0 o 0 o 0 00 I0 010 0 ~ ai
N Dt IA S * 0 0 C U" EC CIO .4C 94 aL Ls a cm La 4 i0 Li=%74 C3L3~~O 0 0 No * a 0 0 91 0 0 aU aO i~CI oO
or 0 9 .4f N*..r NPP3ts.Phc
2F 14,0 %N .. ITNE1-t %0! U% f* La$
t* 02 I0 m 40I III04 C %04 .4 U 1"Opon0%U% a Na v0 e
go L3l %I0mW40 p% * .4 .0U naNtme n"* 0 AI % .t.4hAt & 4 N .4:4.4 aCos e ifL~fff i 43r1clGo
4 0 0 a4 0 *SO 0 c CC 55 90 0 i0*a
WO* Ieml hM 4- N0M"mvv041 C %VIL0 N A* MS0. NA A M00N N"9 M% N a 0' -t*anP,)
di ". .4 .4 rs 0 : a 2i : y C:1S O4 00 0 0 *j 0 5 .. j . * 0 0 * * I
*% t A a 01 47' M* mP P ýNN.4.. N .4.1 n.0 .4 N N0 % " N N. N N Ni
* 0 0 t o * CI'C) iO iJ O iirO )L C 1 ai 0 0 to Li ; Li;; ;
W 5s *ý * * 0 ai s I' C)3 LID Ui UM4' 300 Pic9~Ci )L 1 C -1=42'*)iiC
c~~p L3 -* )Cil C2 C iI0cl *CAt t43 IC112-. v Ir C 3 f r.
0C Li 0. Cl C ji 0 1 el m
-ý- '4 c~ll 7~jA. V.dL: C~Lc C~'lJ- 's 0 0 0 0 0 4*% CA a 9 2 9 3 3 S l 9 m l m -3 9 3 L30 (a 9' 9 3 CA 9 2 9 3 9 Cal
b44.4- ~ ~ N'.'N'',f N )CNJ£A '7I
IL J % Mi. ~~t.
4c 1 ~~ 23
Unclassified - P___$ecun2 Clasification
DOCUMENT CONTROL DATA • R & D(SPCIutaIy eta bslhcaloon of title. &..dp of ..h,rr,* ad ontd o Ing atm .. ,t ,, t - r foer o 'rrd .h. t vrtole 11f l 1 ,It I, ,CtSAsilled)
I ORIGINiAING AC TIVITY (Corporate authut) J20. NFIEOf4 td rUli Tv CLASSIFICATION
The Boeing Company UnclassifiedP. 0. Box 3999 .1 ,Seattle, WA 98124
"3 REPORT TITLE
Propulsion System Installation Corrections
Volume II: Programmers Manual.4 OESCgIP jIVE NOTES .'ry'p* oi report and nuelswev, date%#
Final Report 31 December 1971 to 31 December 19725 AU TNH lIR (First name. middle gntlal. last name)
William H. Ball
* MREPOMT OAtE '. TO?~ Al N O( 8'aGrs [th NO 0? Hl£rs
December 1972 xii + 216 = 229 .Ii. CONTRACT OR GRANT NO V.. OH1IGINA TOWS Fi4t 0004T N•uMIfl RIS
F33615-72-C-1580 AFFDL-TR-72-147b. PROjEC T N0O
C. 3 66S Oth-0Im N IPORT NOISI (Any oth .tnumheta thee may be asI•idesithis frtporl)
d.
10 DISTRIBUTION STATEMENT
Distribution limited to U.S. Government agencies only; test andev luation; statement applied 29 Degember 197 , Other r.quests forhis docuipe t must be re Qrred to Air Force F h Damics Laboratory,
11~1 SUPEETR-OEYsPbNfO0NG i LIAYATV~
Flight Dynamics LaboratoryAir Force Systems Command
-A Wright-Patterson Air Force Base, OH
AAThis report presents the results of a research program to develop aprocedure for use in calculating propulsion system installation losses.These losses include inlet and nozzle internal losses and external draglosses for a wide variety of subsonic and supersonic aircraft configu-rations up to Mach 4.5. The calculation procedure, which was largelydeveloped from existing engineering procedures and experimental data, issuitable for preliminary studies of advanced aircraft configurations.Engineering descriptions, equations, and flow charts are provided tohelp in adapting the calculation procedures to digital computer routinesMany of the calculation procedures have already been programmed on theCDC 6600 computer. Program listings and flow charts are provided forthe calculation procedures that have been programmed. The work accom-plished during the program is contained in four separate volumes.Volume I contains an engineering description of the calculationprocedures. Volume II is a programmers manual containing flow charts,listings, and subroutine descriptions. Volume III contains samplecalculations and sample input data. Volume IV contains bookkeepingdefinitions and data correlations.
DD ,o. ,1473 215 II7nr, + CI
Unclassifiedctruvity Classification
KIEY WORDS LaN. A .gtdFA LINK C
ROLE WT 1401 1 P 1Ot V VI
Afterbody DragBoattail Drag
Bookkeeping Aero-Propulsion ForcesBoundary Layer Bleed Drag
Bypass DragInlet PerformanceInlet Shock LossesNozzle/Afterbody Installation LossesNozzle Interference DragNozzle Thrust CoefficientProdulsion Installation Losses
Spillage DragSubsonic Diffuser LossesSupersonic Inlets
Total Pressure Recovery
iI
Unclassified_216 ,,,• .,,,, ,.. . .