unclassified ad number - dtic · inriine.rino dosrri, ptionw, equations, and flow charts are...

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

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

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.

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

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.;.

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

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

TABLE OF CONTENTS (Continued)

SECTIONPage

KOU14T 186

| DEMAND 189

AREAF 192

AUXHST 194

*IV CROSS LISTING OF PROGRAM TEM 333 196V INLET MAP PROGRAM

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

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.

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

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

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

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

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)

TABU3 - Interpolates F = f(x,yz)

• IFIND - Finds Interpolation Interval

FACINT - Computes Interpolation Factor

CVINT - Perform Linear Interpolation Calculation

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

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~

OF ARRAY FOR LAST

YS MAC H - ALTICALL OUTGOI

DCARD IMAA CA

FE ROR • • O

ONVRT.S |ST

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)

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

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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

T" f EIt)

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WRFI~ 1- UF 1 .75Iah-1).

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Figuire 2: FLOW CHART FOR SUBROUTINE COMPUTE (Concluderd)

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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

Iot It,.

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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

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

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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

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

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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

: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]

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-!.~ .-

0 ý REGLILA FALSIRF ITERATION

-7 2A TO FIND_ 141141) INTERSECTIONJ

NON-CHOKED FLOWAo/Ac C

L R I fA/A)frmCuv

,F c 4e

1:26I > 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

AolAc C

Ao/Ac - A (411

F - FC

SECOND STARTING POINTRF , P141)X2 RF/2

F2- Ao/Ac - DEMAND (RF)

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

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

lq4!. :: ;: I

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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

'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

~AOSy .m

"InAc -Is AAc RF -Ao/Ac = -

Area Wc

' ~RETURN--

Figure 6: FLOW CHART FOR SUBROUTINE AIRSPL

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ha fu.a .

~I Xz ii 00.;

wI O'.2IIII!~ ~i~ 1 0 0-i + itLO0U

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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

Define Built-in ow

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

et 4 Al

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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

ICON -1I

Do j j_

Di 0 9(DBM) 1. + S- I U -

[ Diameter for Inwtference DragDs" D9O0, *

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

• +•'.IL, t i .. Ira

F~m AXHSTIX2)- VA

X2 " ePD

F2 • F

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

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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)

- 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

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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

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

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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

TO; "4 ,,I'

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

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(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

EMF Free-stream Mach number

PTPF Ratio of jet total to free-streamstatic pressure

THETA Boattail trailing edge angle - degrees

ICON f = 0 circular arc boattail

1 conical boattail

SUBPROGRAMS: CABTAB TABUl TABU2

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

La I.I

94 -4 w

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

1.0 100-1

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*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~

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Pv 0 cmmC i"' c I

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b-4 Ii b.- I- N

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,g cc c g e - o - 4

in '4 A 29 9 9 hIoSS3 4aA 0 -1- J 0 V

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

EMF Free-stream Mach number

EMJD Jet design Mach number

PTPF Ratio of jet total to free-streamstatic pressure

TANB Tangent of boattail chord angle

SUBPROGRAM: AL0G CABTAB EXP

SQRT TABUl

< 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

CD -COST + CDs

Figure 12: FLOW CHART FOR SUBROUTINE SUPOT

al. 1 I '* I-

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.4 1- 0 a- ~

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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:

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

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

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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

<0Mach DOT 0-0

tabular Yes CDOT 16 1 palated

option? from tsWe 4.2.1(CALL DBTTB)

plus No CALLCONVERGENTnozzle? NOZZLE MODULE

[CALLCDCONVI

MiKed Yes CALL MIXED FLOW

Flow? PLUG NOZZLE -400.MODULEICALLPLU

CALL NON-MIXEDFLOW PLUGNOZZLE MODULE[CALLPLUGNM)

CR:E T U R tN

figurelIP: FLOWCHART FOR SUBROUTINE DBOATR

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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

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

pW~mb'o 1.0

M>h, 1.0

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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

F 16: FLOWCART 1.0 O T NT

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Now: O €omped by boattaN drag rouimn

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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

N ot:SA041 is Ynt 0ififdootr4. .4

Fr7%-1SFL CAR SUBOU

Note: ABASE is Input In field 8 of card 4.,1.1

i ~FigurelA7 FLOW CHART FOR SUBROUTINE DBASER

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.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.

eq 0.e Ir 4C 40

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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

Twb 618.0 - .0=03618 ALT

Twn T - 364.18 + .0006M3 ALT

ALT: 10002 30.4757 - aG43Tam

> 100000

it IiN

Figure 18. FLOW CHART FOR SUOROUTINE ATMOS

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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

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

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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

a ft 41 L~- (ý c' . . ..- vs.ca-w-0,--..-

*4 .4 m M" P n"inq",44rr*r ttU%% UL

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0. 441 14

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lOP- 0 4 N Z! 0 Q CDPe 'r I- vi 4V1 or v- z S. y I. OY li

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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.

I~ 4 OA.I I

10 IA I WI

lA l * UU &f # s

e Sl ýý-p 0%. Al

0, PIS0On .,

coaw '-

(1., C

'4wtto

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.

I, 0,0

r2 42 co at C2

C, C3 402 olu

~,.-.-. .- - ~--.----.--~---c

9 ( I 'I I I I

I I I, 1

-~ I I I j i

(A 49 I- 0 OA

I l f W I I

a 11 z IA

at IA Iw r--

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

'7" .-

vS I,' ~

us A , W

w 0,ILI

00i . it

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

II Iz I -,I. lcl 1, 0za 44r lý(L (A U.0so0 4aeb-½, 3

ca IA c

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;IV If% ILb. uj 2

0 , Co 0 v .

cz 21, w a.~ 0

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

IOutput (continued)

V2 Nozzle ideal exit velocity ft/sec

A Nczzle throat area ft 2

FG Gross thrust lb

SUBPROGRAMS: AREA H0FPR SQRT

* PR2 - (PRI)(P~,.b)

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

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

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- 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.

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

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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

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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)

T can be specified in the calling program by

either:

DIMENSION T (2MAX) or C0MM0N/T/ TX(MAX),TY(MAX)

SUBPROGRAMS: PLACIN

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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.

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)

SUBPROGRAM: PLACIN

,, 147

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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

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

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

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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

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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

I A- tI !I

Q I' lI 'g f

... I.

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.

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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

I. II0 I

.- w 1-

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

o4 Z da " -4 *4 to -Z

CJ3V-'40 I.)

0 49 T b ofUILb-10 0 il2

w z x le187

s qrW z V

V) 41 I2 w t

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

USAGE: A0AC = rvMAND(RP)

RF is recovery factor

Area = AREAF (Mach)

WC = Engine airflow

W S •Secondary airflow

AC = Capture area

SUBPROGRAMS: TABU2

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

InK I 'wco caU

ty Li09' C

C. 0.4

Ip C% 93

ra ft 0

-W ., T O .W

i* 4K .1

;In -Ses f '.a C , -oC

" D 3 2I,

63 43 aC3 ca EK

* 44 i92

I I - 'I .

o III ' I t

tA o. . -IA .

j Is I

i Io I

L2 b-3 I I jI41193

III, I

* . .. , I

* I, S. I.Z4 I

* g 1•s I

* ..I II,,, a

,I 1 i• 114 %1.,! I .

F"J . - rlll, r 1- •

bD 0 Dn

13 0 - 03

.. *Z 311 4m

'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

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CY AD.N N e4 N N

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SECTION V

INLET MAP PROGRAM

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

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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 ____________________

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 ___ ________ ____

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

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

-- - - -- - =

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CA alC, " CAC rj c, e. C., 440 cV CAI cm 196) 'rb~' ast Cft

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- 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.,

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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)

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

Unclassified_216 ,,,• .,,,, ,.. . .

unclassified ad number - dtic · inriine.rino dosrri, ptionw, equations, and flow charts are...

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