0OO
NASA Contractor Report 172213

MINIVER UPGRADE FOR

AVID SYSTEM

t'..J . r _" "_*

THE

VOLUME I1: LANMIN INPUT

GUIDE

Carl D. Engel

Craig P. Schmitz

REMTECH, Inc.

Huntsville, AL 35805

Contract NAS1-16983

August 1983

-, =

i

N/ A

:-;-_-¢ :-2_ _ <_t'a' 3-

L_ngley Research Center

_-13_o_
FOREWORD

This final report presents work which was conducted for angley Research

Center (LaRC) in response to requirements of Contract NAS1-16983. The work

_resented was performed by R/_h'TE(_, Iuc.

''MLNIVER Upgrade For The AVID System''.

voltages.

Volu_e I:

Vo 1 _.me II:

Volume III:

Huntsville, Alabama and is entitled

The final report consists of three

LA._M_ User's _tanual

LANMIN Input Guide

EXITS User's and Input Guide

The NASA technical coordination for this study was provided by Ms. Kathryn

E. Wurster of the V.-hicle Analysi_ Branch of the Space Systems Division.
TABLE OF CONTENTS

VOLUME I1

LANMLN EqI_T G_IDE

-_ CT]ON PAOE

1 . 0 LNTRODF CT ION ........................ I

2.0 CARD LNt:K'T ......................... 5

3,0 PREPROCESSOR D;TER_A.urB'E D41::'FT, .......... 20

1

3.2

3.3

3.4

3.5

3.6

3.'7

3.8

3.9

MAIN ......................... 20

S_BROVT L-NE LNI_T ................... 21

SUBROUT LNE VOD IF'Y .................. 21

SUBROVT LNE TZMING .................. 21

SUBROUTINE TRAJ ................... 22

SUBROUT _'E ATMS ................... 23

SUBROUTINE W,NI)TEN .................. 23

SITBROUT INE ATRDTA .................. 23

SITBROUT INE HEAT IN .................. 93

3.10 SUBROUTINE BTRMTD .................. 24

3 . 11 SUBROUTINE BTMULT .................. 24

3.12 SI3BROIY[LlqE TRANS ................... 24

3.13 SUBROUTINE CROSS ................... 25

3 . _ 4 S17BROL'_.t.RE FLOW ................... 25

3.15 S13BROUTL-NE TIM;EOM .................. 26

3 . 16 SUBROUTLN[ CONTRL .................. 26

3 . 17 SUBROUTENE UNITS ................... 26

3.18 SITBRO_TINE STREAM .................. 26

3,1 9 SFBRGFTLNE Ot_TtK-T .................. 2"

4.0 OV'l'lmTT DESCRIFflON .................. 30

APPEND IX

A, W (ARRAY DEFINITIONS) .................... A-l--A-7

B. S._RPL E CASES ........................ B'-l_B-49

1. HEATLNG L-x,'DICATOR S/Lkt_E CASE .............. B--1

2. WLND TITN_ SAKPLE CASE ................. B-14

C. PREMIN LISI ING ....................... C-1_C-46

li

II_-z=.
Section 1.0

INTROD_ CT ION

-T

The serot_ermal software developed for use in the AVID system (Ref. 1) is

doc_ented in three volu_es. The first vo1_e provides a detailed description

of the Langley version of ML_IVER (LANHI_). Vol_e II provides a users input

guide to the LANMIN code, and Volume III gives a descriptiou and input guide for

the Explicit Interactive Thermal Structures (EXITS) code,

The overall information flow for the aerothermal software in the AVID system ,s given in Fig. 1.1. Vol_es I and II cover the componentz within the

dashed lines of Fig. 1.1, and Volume III documents the remainder of the

software. As shown in Fig. 1.1, the input to L_NMIN is -_de via an input file,

This file is a card image and thus can be treated as card input as discussed in

Section 2. The preprocessor's prime function is to ,,roduce this input file. A

description of how to use the preprocessor (PREbtLN) is given in _,ction 3, The

output from LA,N_IN is documented in Section 4.

The LANMLN program consists of 51 routines and one main program. A comparison of the set of LA,NMIN routines with the MLN_'LR routines is given in Table

1.1. The conduction related routines were eliminated from the _INI_T_R code when

generating LANMIN. All c_nduction related routines were incorporated in the

EXITS code documented in Volume III. Thirteen routines which were retained from

the original }4INIVER code have been modified. Twenty-two new routines have been

added to the code in creating the LANMIN version.

"lhe flow diagram for the LAN_IN code is given in Fig. 1.2. Functions and

block data are listed to the side. The diagram shows the calling hierarchy for

the subroutines. The input to LANMIN is through the KAIN. An output file :an

be crested and it is generated in VA._OUT.
Table 1,1

L.KN'_EN .'_ IN G'ER SUBROUTL_ES

LA._ L_

AFR62

AT._S4

BLOCK

BLOCKA

B LNTRP

BTE I CK

CONE

CPIAF

CRSFL)

CYT

DEFL

DETRAL

DOWNID

DSTML

DWNST_*

ECKERT

EDPAI_

ERF

FAYRID*

F_q]

F LNPKII

F LNPKP

FLAPIt

FLO_*

FilttEAT

FSUBC a

ItANSEN*

ML-_IVER

AUR62

ADDS4

CRSFLW

DETRAL

DENT

DLNTI

DOWNID

#DRIVEL

DWNSTI_

ECKERT

EDPARM

FAYR ID

#'F INALT

FLOW

FSUBC

#GUASS

II.A_SEN

#L_ovrR

L4_N._.EN MIN IVER LAN_ IN ._L_; TVER

L_TP1

L\"f'P2

LESIDE

.__aD;"

MOLIER*

PCSW*

PMEKPbl

PMID

RA.DEQT*

P_3 LME

RHO,_R

SLOPE

SPCIt I*

SPFP

STHY_.AT

H800

#_L_TRES

MOL LE R

#._PROPS

#OPT_YZ

OV LAV O 1

0V432

PCSW

PLO'IS

PMIXPM

PbIID

#PR IN_fA

RADE_T

I_OMUR

#SETMUP

SPC_I

#STABLE

#STOCK

S_CYL

SWCYL2

SWCYL3

TBLIN

TINT6

V.__NOUT

VRA71

VRE':_

_'R ENP*

SWt'YL3

-r'BLL-N

qT6

IKs,.N S

WRLNI

WRTOI'I

WYROS

*These Subroutines Have Been Modified.

#Conduction Related Subroutines.
OR,,_ .......... ._

OF POOR Q'JALITY

F

I

I

I

I

I

I

i

I

I

I

i

I_-.

I

I LAN_:N PREP;Z:_E._J_

i

t PEM:N

h

i

LAN_:N FILE

F

; I

1

r_,E

riLE

I

I

t

I

_F V_ &If _es

I

I

I

I

!

#STPcC_UQ ES #

FILE

I

t

L I

OL"_" I PRCPERT':

FILE I DATA BASE

l

OCTPL'T

CO_E F:LE

Fig. l.I Overall Information Flow

3
3{'- F ....,_R

r

1

E

o

I.a_

L

U
Section 2.0

CARD LNPt_ T

The card input to L&N_IN has been broken into _ixteen functionmJ areas.

_nese areas are as follows:

(i)

(2)

(3)

(4)

(5)

(_)

(7)

(8)

(9)

(10)

(ii)

(i2)

(13)

(14)

(15)

(16)

Title

Timing Pars.meters and Print Control

Trajectory Data

Atmosphere Data

Flowfield Options

Flow A._gle Data

Angle of Attack Option

Crossflow Data

Transition Criteria

Heat Transfer Options

Heating Multipliers

Transformations

Surface Condition

Gecmetry Data

Initial Conditions

Control Parameters

Most of the input for these areas involves specifyin_ the values for the 'W'

array. A definition of all the elements of the 'W' array is given in Appendix

Ao
P

s

(1) TITLE

Format (18A4)

Case De _cript ic,n

(2) TIMIN_G PAtL%.KETERS AND PRR!h_f COhq'ROL

For=a t (3F20.6)

CARD COL UM_

NO.

L', P[ T VALUE

1-20 tl

21-40 /,tl

41-60 t2

Initial time, lec (W(1))

Printout interval 1, sec (W(2))

Second time, aec (W(3))

1-20 At2

21-40 t3

41-60 At3

Printout intervll 2, sec (W(4))

Third time, see (_(5))

Printout interval 3, aec (W(6))

1-20 t4 Fourth time, sec (W(7))

21-40 kCALC Calculation interval factor (_(8))

Note: If less than three printont intervalz are desired,

the unused 7arameter must be input as zero.

(3) TKAIECTORY DATA

Fort-at (3F20.6, 2FIO.E)

CARD COLL'3tN £NI_T VALUE

NO.

1 1-20 Number of time dependent table entries (W(50) limit _ 50)

J,

t

1-20

21-40

41-60

61-70

71-80

Time (t), sec (W(51)--W(100))

Altitude (z), ft (W(IO1)--W(150))

Velocity (v), ft/aec (W(151)--W(200))

A_gle of Attack (a), desrees (W(211)--W(260))

Ya- gmgle (_), degree, (W(651)--W(700))
(4) A_OSPHERE DAT_.__AA

Format 5(13, F10.6)

LOCAT ION

FORJ_AT (13 )

OFrlON OR DATA

FORMAT (F10.6)

el0 A:mosphere/Freestream Properties Option Flag (ATFLAG)

O. Freestream properties are defined usin8 the _

Standard At¢osphere. Trajectory data are required i_put.

1. Wind tunnel input option -

Freeatream static temperature and presage are input in

locations 451-500 and 501-550, respectively, as a function

of _ime. The time data and freestream velocity data are

input in the TRAJECTORY DATA card set with the altitude

(z ) set equal to zero.

2. Fzeestream static temperat_e and pressure are input in

locations 451-500 and 5b±-Sb0, respectively, as a function

of altitude. Altitude values are ivput in locations

401-450. Trajectory data (time, altitude, velocity and

angle of attack) are required input.

4. F_eestrean properties are defined using l'h_...._o_9_3 Pitr!¢k

Air Fo_ce _ (P_B) Atmosphere. Trajectory data are

required input.

$. Freestream pro_ertles are defined using Th__.ee_Lg_._an_enberl

Reference Atuos_here. Trajectory data are required input.

6. Freestream properties are defined using Th___e1__ yandenberl

Hot Day _tmos_here. Trajectory data are required input.

7. Freestream properties are defined using Th_._ee_ yandenbera

Cold Day _tm9%phereo Trajectory data are required input.

8. Freestream properties a_e defined usin$ The _ Kennedy

Ho___tt_D__y Atmosvhere. Trajectory data are required input.

9. Freestream properties are defined using Th.._ee_o_ _ennedy

Cold D ly _mcaphere. Trajectory data are requ1:'ed input.

400

401-450

451-$00

501-550

Freestream Properties Data Input as Follows:

Number of table entries (Li_it 50) Enalt,

Table of altitude data, ft

Table of freestream temperatures, R

Table of freeatream pressures, lb/sq ft
( 5 ) ___I_La) oPTio._s

Format 3(I3o F10.6)

LOCA T ION

FORMAT ( 13 )

OP'FION OR DATA

FO I_ttAT (F10.6)

031-036

046-048

F!owfield and Local Pressure Option Flags (FF)

Flowfield and pressure option flags are input beginning in

Location 931. A tots1 of 9 locations •re ,vailab!e

(031-036 and 046-048). The first flo-field option flag

must be input in Lozation 031, foilowed by additional

flowfield and press u2re option flags, as needed. Location

number must be used in ascending order, Flowf!eld and

pressure flags always occur in pairs except for FF = 39

(Swept Cylinder) and FF = 29 (Prandtl Meyer expansion).

Flowfield Options:

35. Sharp Wedge Shock Angle.

_he shock angle for • sharp wedge is determined from •

built-in table of sharp wedge shock angle as a function

of u_stream Math number and the _edge or flow deflection

angle. Fhe wedge angle is input.

36. Sharp Cone Shock Angle.

The shock angle _or a sharp cone is determined from an

internal table as a function of the cone half-angle and

the upstream Much number. The cone half-angle is input.

38. Oblique and Normal Shock.

The actual shock angle is input.

• normal shock.

Q

An angle of 90 *2pre-.,nts

39. Parallel Shock.

_sed alone or as • last option to indicate that • wwept

cylinder or parallel shock solution is desirp_ (no pressure

flag seeded). The angle-of-attack or shock angle is input.

For swept cylinder the input angle is the (90-k) where

k is the sweep angle in degrees.

D

P

8
L_ _ _ _._

LOCATION

FORMAT (13)

OPTION OR DATA

FORMAT (F10.6)

031-036

046-C48

Local Pressure Options:

14. INleT Cp as a function of H_ for the location W(649) = 1.0,

Data Stored in TCP_( ) = Cp, T_dCP( ) = M_ , NCP_I ". = nu_zber of

Rach Numbers.

l_. Tangent _edge Pressure Coefficient.

The local pressure coefficient iors tangent wedge is determined from a built-in taSle as a function of the wedge angl_

and the upstream _s_h number. The wedge angle is input.

16. Tangent Cone Pressure Coefficient.

The local pressure coefficient for a tangent cone is determined

from a built-in table as a function of the cone half-angle and

the upstream Math number. The cone half-angle is input.

17. Oblique Surface Pressure.

Provides pressure solution for a surface whose shock angle is

slightly greater than the surface angle-of-attack or flow deflection angle. The shock angle must be known and input under

the flowfield shock option (flowfield option 38). The input

pressure angle is the surface angle-of-attack or flow deflection

angle.

18. Modified Newtouian Pressure - Oblique Shock.

Local pressure is ca!culated as a function of the local slope.

Local tot 1 pressure is used with this option.

The local _ody angle is input.

Prsndtl-Meyer Expansion:

2_.._'hia option provides a Prandtl-Meyer expansion and is used follo_ing any one of the local pressure options. The input angle

is the angular difference b_tween the t_o slopes (flow turning

angle).

(6) FLOW ANG_ DATA

Format 5(I3, F10.6)

LOCATION

FORMAT (13)

OPTION OR DATA

FORMAT (FIO.6)

037-045 Flow Angle Data Input.

The angles required as input by the flowfield options are input

beginning in location 037. These data must be input in the same

order as the flowfield option location requiring their input.

fi.e., the angle input in location 037 must correspond to flowfield option in location 031, etc.). All angles are input in

degrees.
(7) _NGLE OF All'ACE OPTION

Format 5(13, FI0.6)

LOCATION

FOR_V,_T (13)

OFrlION OR DATA

261

262

263

264

265

266

267

268

269

#mgle-of-Attack Option

#_g!c: _np_t in Ic,ca:i. czs ¢37 azd 077 _:e _Zj;s:ed _i:t;:

the _c,$ra_m to accost for an_le-of_attsck. _f it C,_

desirable for other a_gles _ny_t in Ic.catio_s 0_9 thrcx_h

045 to be adjusted for angie-of-attack, _he f:_:owing

control p_r_L._eters must be inpu::

l, Initialized in _ain

2. Imitialized in _ain

3. Varies A_gle in Location 039 (i_pnt data)

4. Varies angle in Location 040 (input data)

5. Varies angle in Location 04: (input data)

6. Varies angle in Location 042 (input data)

7. Varies angle i_ Location 0_3 (input data)

8, Varies angle in Location 0_ (Input data)

9. Varies angle in Location 045 (input data)

]$
(g) q_OSSFI_OW

Format 5(I3o F10o6)

LOCA T iON

FOR_,T (I3)

OFT ION OR DATA

FORMAT (F!0.6)

lb

202 Croasflow Option Flag (CFF'LG)

1. Constant Width Re2tangle (Ideal Gas).

This method ass u_ts a constant width rectangle and idetl

gas chordwise velc,_ity gradient. Required inputs are

corner radius, Rc, and vidth, D.

O

20 Constant _tdth Re:tangle areal Gas).

This _ethod assmm_s a constant width rectangle and

r_al gas chordwis_ velocity gradient. Required inputs

are width, Do, and the velocity gradient correction

factor, U. The term E can be varied from 0,31 for •

flat surface to 1,0 for a swept cylinder.

3. Sharp Edged Delta Co,figurations (Ideal Gas).

This method assumes a sharp edged delta configuration

and ideal gas chordwise vale, city gradient. Required

input it the delta sweep angle X.

4. Delta Configuration (Real Gas).

This method assumes a delta configuration and real gas

chordwise velocity gradient. Required _nputs are the

delta sweep augle, X, and the velocity gradient

correction factor, _. A sharp edged delta configuration

is representeJ by U=0.31. An input of fi=l.O produces

croasflow on _ printed cone whose half angle is (90-X).

202

203

204

205

Crossflow Data Input

Rectangle Width. D (ft)

0

Delta wing sweep angle, _ (deg)

Real Gas velocity gradient correction factor,

Rectangle corner radius, Rc (ft)
(9) I'KANSITION CRITERLk

Format 5(13, FZ0.6)

LOCAT ION

FOICK_T (I3 )

OPYION OR DATA

FO_IAT (FI0.6)

O27 Transition Criteria Option Flag (TRFLAG)

I. T_is option allows transition from laminar to turbulent flow to

occur at a particular time in the trajectory. The time (see)

when transition begins is input in Icc_tion 0!4. The time (see)

when fully turbulent f]ow is reached is input in locati_n 0_0.

2. This option _s,tion is is the la_e as option 1, except tr.- 4 from

turbulent to laminar.

3. Trsnsitioe 3ased on the Reynolds n'_mber R .. Input requirements

e

are the onset Reynolds number (PA_, loca_iou 014) and the fully

tmrbulent Reynolds number (PARA2, location 020).

$

4. Transition based on R _ . Input requirements are onset

Reynolds number (P u_ location 014) and the fully turbulent

Reynolds number (PARA2, location 020).

5. Transition _ased on _ (_fl)AC-E transition parameter). Required

inputs are the onset value of _ (PMLA_I, location 014) and the

fully turbulent value c_ _ (PARA2, location 020). The par_eter

is defined by the equation,

• )0.2]

= Re__ [M e (PeUe/_e

6. Transition based on ¥ (see option 5). Tran,ition onset

determined from built-in eucv.e of _ as a functic_ of angle of

attack, The parameters PARA1 and PA_RA2 are n_t re !uired inT_t.

Transition zone length is determined from the ratio,

LFFLLY T_B/LT_._'S ONSET

This ratio is input in location 028, if desired, if n_ value is

input the program will select a value from a built-in table of

_ogxo R _ versus ratio.

¢ _

7. Transition based on built in cur,_" datp, of onset ReT R versus

M (Rockwell International criteria). Transition zone length

determined in th_ same manner as option 6.

$

8. Transition based on R _ /M . Input requirements are onset

value (PA_I, locatio_"014_ and the fully turbulent value (PA2A2,

location 020). Nominal values are 150. and yt_-x 150 reapectivaly.

Transition Data

014 PARAI

020 PARA2

028 Transition Zone Length Ratio

-- 4

L
(Io) _ _:'PVU_SFEROPTIONS

Format 5(13, F10.6)

LOCATION

FORMAT ( 13 )

OPTION OR DATA

FOR,_AT (F10.6)

011 Heat Transfer Method Option } 5g (HTFLAG)

1. Fay-Riddell Stagnation Point Method.

Required input data are nose radius Rq (location 012) and

flowfield options 38 and 18 with ahoci and pressure angles

of 90 degrees. An option available (location 315) will

allow dissociation to be considered (Lewis no. = 1.4) or

not considered (Lewis no. = 1.0),

2. Care/Johnson Swept Cylinder Method.

Required input data are local cylinder radius _ (location

012), sweep angle X (location 017), flowfield o_tion 38

with a shock angle of 90 degrees, and flowfield local

pressure option 18 with a pressure angle of (90-X) degrees.

3. Eckert's Reference Enthalpy Flat Plate Method.

Required input data are the running length (location 013)

and Mangler transformation factors for both l amina_ and

turbulent flow (locations 01S and 016, respectively).

4. Eckert/Spalding-ffhi Flat Plate Method.

Required input data are running length, L (location 013)

and Mangler transformation factors for both laminar and

turbulent flow (location 015 and 016, respectively). If

the Von Karman Reynold's Analogy factor is desired,

input a 1.0 in location 319 otherwlae it uses Colb_rn's

equation.

5. Boeing p _ Flat Plate Method.

r

Required input Is the r_ning length L (location 013).

6. Modified Beckv_th/Gallagher Swept Cylinder Method.

Required input data ate local cylinder radius RN (location

012) and flowfield option 39 with a shock angleof (90-_).

7. Boeing pry - Swept Cylinder Method. r

Required input data are local cylinder radius R_

(location 012) and flowfield option 39 with a a_ock angle

of 90--k).

8. Lees, Detra and Hidalgo Hemisphere Method.

Required input data hemisphere nose radius RN (location

012), running length L (location 013), focal'body slope 6

(location 017), flowfleld option 38 with a shock angle of

90 degrees and flowfield option 18 with a local slope angle

of 5.

13
9. 8ertin and Goodrich, Leeside Orbiter Heating.

Requires Fay and Riddell input (R_ = 1 foot for f-_!l scale)

and wi.adward wail enthalpy for W(_I)_ If W(21) = 0.0 during

input, W(21) = 480 BTIT/lbm (2000OR _,all).

I0. Bushnell and Welnstein, Fla_ Reattackment Beating.

Input i_ the s&_e as for b t transfer option 4 pi_s Flap

length is input in W(22). Running 'ength is to the hinge

line. If separation and reattacb.ment does not occur, option

4 methods are used.

Ii. Five/, Fin-Plate Peak Interferenct Heating. Input is the

same as option 4, which is the default option if th_ fin

shock detaches, plus special valnes for this option.

IF _(30) = 0 the fin angle is used, iF W(30) = 1.0 the

angle of attack is added to the f:_ angle, and IF W(30) = 2.0

the yaw angle, 8, is added to the tin angle. The length

from the fin leading edge to point of interest along the

fin is input in W(25). The fin angle relation to the

local flow at a = _ = 0 is input in _(26).

315 Dissociation Option

This option is _sed with the Fay-Riddell stagnation point

equation (/_TFLAG - 1.0, location 011).

O. Dissociation considered (Lewis nr_ber = 1.4)

I. Dissociation not _onsidered (Lewis number = 1.0)

.......... o- "-_
(11) IIF..AT!NGMULTIPLIERS

Format 5(I3, F10._)

LOC.AT ION

FORRAT (I3 )

OPT ION OR DATA

FORMAT (FI0.6)

018

el9

320

321-330

331-340

341-350

360

361-370

371-380

381-390

Multiplication Factor Input

Heat transfer _ultiplication factors can be input as a

constant value, a function of trajectory t£me and/or a

function of upstream bach number. All three input options

may be used, if desired. All multiplier values are

multiplied together to obtain an overall value.

Constant M_ItiplJer (LmmJn_r)

Constant _ultiplier (Turbulent)

Number of Time Dependent Table Entries (Limit 10)

T£me Table, sec

Multiplier Table (Laminar)

Multiplier Table (Twrbulent)

Number of Mach Number Dependent Table Entries (Limit 10)

Mmc_ Number Table (Loglo M )

Multiplier Table (Laminar) (Logle hi/hu)LA M

Multiplier Table (Turbulent) (Losx o hi/hu)TURB

15
(12) TRAN.SFORRATIONS

Format 5(I3. F10.6)

LOCAT ION

FORX_T (I3)

OPTION OR DATA

FO RY_ T (F10.6)

319

029

Reynold's Analog_ Factor

0. Assumes Co!burn's Reynold's Analogy factor defined _s

S = (P) (Generally used for design_ r

I. Assu_es Von Karman Reynold'a Analogy factor defined by

!

S = I + 5(Cf)" [(P - 1) + In ([5P + 1]/6)] r r

(Generally used for prediction)

Virtual Origin Option (VRFLG)

O. Uses tke geometric r_nntng length in the heat transfer equations.

1. Corrects the geometric running length to account for the onset of

transition. Uses the corrected running length in the tu bulent

heat transfer equations.

Mangler Transformation Factors

Laminar Factor = 3 Cone

Turbulent Factor = 2 Cone

(13) SURFACE CO,_I)ITION

Format 5(I3, FI0.6)

LOCATION

FORMAT (I3)

OFTION OR DATA

FORMAT (FI0.6)

021

023

Windward Bottom Centerline Wall Enthalpy (Btu/lbm).

Used with heat transfer option (9) for orbiter leeside heating

Materlal Emissivity

Emisaivity (must be > 0.0)

16
(14) _ ._._T..AA

Format 5(I3, F10.6)

LOCATION

FORKAT (I3)

OPTION OR DATA

FORMAT (F10.6)

012

013

017

Geometry Data Input (Constant)

Nose or Ledding Edge Radius, ft

Geometric Running Length, ft

L<)cal Slope or Sweep Angle, deg

560

561-570

571-580

581-590

591-600

601-610

354

Geometry Data Input (Function of Time)

Number of Table Entries (Lia_it 10)

Time, aec

Nose Radii, ft

Running Length, ft

Local Slope or Sweep Angle, deg

View Factor (not used)

Surface Distance to start of turbulent boundary layer. The

value input in location 354 is subtracted from the total

running length input in location 013 to provide the new

running length for turbulent heating.

(15) .IN_L,p.,CO_ITIONS

Format 5(I3, FiO.6)

LOCATION OPTION OR DATA

FORMAT (I3) FORMAT (F10.6)

@

024 Initial Temperature, F

316 Integrated Convective Heat Flux, Btu/sq ft

17
(16 ) _,OhTROL PARA_TERS

Format 5(I3, FlO.6)

LOCATION

FOR_T ( 13 )

O_rlrlON OR DATA

FO I_KAT (FI0.6)

299 C_ntinui " Option

0. Convective Heating Load initialized,

1. Convective Heating Lo_d not initialized,

314 Rarefied Geometry Option (\TCS)

0. Sharp cone rarefied equations used

1. Flat plate rarefied equations used

611 Body Point Number

641 Program Input Control Parameter (JFK)

This parameter must be the last entry in the Control

Parameter Card Set (must be > 0.0).

1. Read new case data using title, timing parameters

and trajectory data f_o_ previous case.

(Uses all unchanged case data from previous case.)

2. End of input data (use with last case).

3. Read new title and timing par_eters and use trajectory

data from previous case.

(Uses all unchanged case data from previous case.)

4. Read new title, timing, trajectory and case data

(Initially zeros full W array)

5. Same as 1 (except zeros all case data from previous case).

6. Same as 3 (except zeros all timing parameters and case

data).

642 Print Option (3FO0)

O. Normal Miniver printout

1. Normal Miniver printout plus V_NOUT (summary) printout

2. V_IOUT printout only

18
643 0, No output file from VANOUT created

1. OUTPUT FI]-E fro,, V&_OUT created

646

648

649

Rarefied Flow Option (NONCON)

0. Continua= flow equations are used throughout flight

!. Contin_= and rar*fied flow eq_.ations are used,

d_-pendin$ on flow regime enconntered during flight.

Output Units Option

O. English

I. Metric

Pressure Coefficient Input Option (YFCP)

These cards follow 641 specifications

Card 1NCPI_P (I3)

Card 2 M_, CD (2F10.6)

Card 3 M=, CD (2F10.6)

O, Pressure coefficients are not input

1. Pressure coefficients are input (Flowfield option 14).

650 Cone Flow Option (NSB)

Thit option is used only when rarefied flow conditiont

are considered (Control Parameter 646.)

O, tTsea sharp cone correlationa

1. Uses blunt cone ccrrelations

19
Section 3,0

PREPROCESSOR I_q"EKACTI'VE INPUT

This _ection contains descriptions of the subroutinez used by the pt:processor code _IN. _[_F_,IN is an interactiv: preprsc_-ss:_r _cde for :,_IN.

FP_IN creates a file that is in the same card image format as discussed in Section2.0 and i_ u_ed as the input f:le for L.&\'MLN. T_e prim._ry information included in this file I$ the '_' array. A definition of all the elements of the

'W' array is given in Appendiz A.

The PRF__IN program consists of 18 routines and one main program, and is capable of c_eating a new output file oz modifying an old one. T'ne routine INPUT

is used to input the file to be modified and the routine OUTPUT is u_ed to

create the output file. A macro flow diagram of PREMIN is i_cluded in Figur_

3-1.

3.1 RAn_

NALN performs the task of mana$ing the rest of _tF__M_N. 7he d, cer_-:nation

of whether PREMIN is to create a new output file or modify an c;d uutput file is

made within MAIN. After the method is determined, _IN sal]_ the required

routines in their proper sequence a case at a time. The variables transferred

in Co.on or used as control fla_a by MAIN _=e:

IIN - Interactive Input - FORTR_ Unit Number

IOUT - Interactive Output - FORTRAN Unit Number

]_r'0 - English units

KFLAG=I - Metric units

FLAC-_O - Create new output file

FLAG=I - Modify old output file

JFLAG=I -Previous case deleted

INSERT=I - Current case inserted

TFLAG=I -TYrL1 currently defined

FNAM6 NLme of input

JFKS - Program Input Control Parameter (W(641)) for the

previous case

2O
f

NC

ND

NI

TITL1

NCPMT

NCP_frs

TMCP

TIdCPS

TCPM

TCP_IS

W

irw

- Case number

-Number cases deleted

- Number cases inserted

-Title of s set of cases

- Number of Mach numbers in CP vs. blach number table

- Saved value of NCP_flr from previous case

-Mach number array for CP vs. Mach number table

- Saved _alues of T_CP array from previous case

- CP array for CP vs. Mach number table

- Saved values of TCPId array fro_ previous case

- Array of values created and modified by PREJdIN

(always in English units) (see Appendix A for complete

description)

- Final array copied to output file. Copy of 'W' array

except changed to desired output units.

3.2 SUBROUTINE INPUT

Subroutine INPUT is called by gain and performs two functions. If IB which

is the parameter passed in the subroutine call equals 2 then INPUT zeros out the

values in the W array according to the Program Input Control Parameter of the

last case and returns to RAin.

IF IB=I then INPUT reads an existing L/uNMIN input file for the purpose of

PREMIN creatin| a new ].A_M!N input file. INPUT first zeros out the N array according to the Program Input Control Parameter of the last case and then reads

in data for a single case from the input file. INPUT keeps track of the current

case number and inserts and deletes cases.

3.3

case.

specific section of the N array.

of a specific V number.

SUBROUTINE MODIFY

Subroutine MODIFY is called by gaIN to m6dify the W array for the current

I/ODIFY calls a requested subroutine in order to modify or redefine a

gODIF¥ is also capable of changing the value

3.4 SUBROUTINE TIMING

Subroutine TIMING is called by KAL-N or MODIFY to define the Timing Parame21
ters and Print Control values. TL_LNG assigns values for ¥(I) through W(8) and

checks to see if the number of print times exceeds I00. SF_ equals the total

number of print times.

3,5 SUBROt-[ L_E TRAJ

<':t-outine TRAJ is called by MALN or ,_ODIFY to define the trajectory data

to be used. TIL_5 obtains this data from a uses supplied trajectory file or intersctively via the terminal.

If the trajectory is read from a trajectory file, TRAJ first deternines

whether Beta data is included and the number of time dependent table entries,

them reads ALT, V'EL, Angle of Attack, and YAW Angle (if included) for each

TI._IE. After obtaining the trajectory data from the trajectory file, TRAJ will

display the trajectory data on the terminal 20 lines at a time waitiug for a

carriage return between pages. After display TRAJ gives the user the opportunity to modify the trajectory data.

The format for the trajectory file is an Ago for the title on line one.

Line two contains the Beta flag usins an 12 and the nr,mber of trajectory trees

using an F10.5. The rest of the file contains the trajectory data u;in_ _itber

a 4E1_.4 or a 5E15.4, depending on whether or not the yaw angle 3ata is included.

The other method of crea¢ing the trajectory data is via the terminal by inputting a line at • time. After defining the trajectory in this manner, TRA]

proceeds to display the trajectory data on the terminal as described above.

After the trajectory data table is displayed on the terminal, the user is

given the opportunity to modify part or all of the trajectory. TRAJ enablea the

user to insert, delete, or change a line of the trajectory. After modification,

the trajectory "_s displayed on the termirual as before.

22
L

Once the user is satisfied tba_ th_ trajectory is complete TRA3 will enable

the user to create a new trajectory file with a nevr use_ supplied file name.

The variables used in TRA3 are:

FNA._ -The fi!eaame of the trajeetor file.

II-_T - The number of t line at the trajectory table.

TITLE - Title of the tro_ectcry file.

BFLAG=I - YAW Angle included with _rajectory.

3.6 SYBROUTL'_ AT_S

Subroutine AT_IS is called by _¢ALN or MODIFY to select the Atmosphere option

to be used.

3.7 SUBkOUTINE WNDTUN

Subroutine ]D_DTUN is called by MAIN or MODIF _ if the Atmosphere Option 2

was selected. VNDTUN defines the Atmospheric data for a Wind Tunnel case.

_TUN sets values for T_ and P_ for each time point of the trajectory NPTS is

the number of t,me points.

3.8 SUBROUTinE ATMIYTA

Subroutine ATMDTA is called by MAL-N or MODIFY if the Atmosphere Option 3

was selected. ATMDTA is the routine the user uses to define his own set of Atmospheric data. AT/_TA asks for the number of Altitude entries (_ALT) and then

asks for the values of Altitude, T_ ,and P_ for each entry.

3.9 SUBROUTLVE HEATIN

Subroutine _,_,A_LN is called by MALN or gODIYY if a Heatinj Indicator case

is desired. HEATIN sets the 'W' array values for a I ft_ radius s_here with a

0

wall temperature of 0 F and a Lewis number of 1.0. HEATIN uses the Heat

transfe_ option 1 which is the Fay and Ri_deI1 Stagnation Point getbod. HEATIN

23
0

uses the OBLIQUE Shock Flowfie]d option with a _hocL angle of 90 . The _odified

O

Ne_'tonian Pressure option is used ,i%h the body an_le of 90 KE_TEK sls_ se:s

the Print _ption to 2 vhich sets the o_tp_t fvr S_arv Print only.

Subroutine _.m-_D i_ called by' ,_.AIN or ._ODIFX to select the _eat Trazsfer

M_hod to be used. ET_D sets the _alues for the _arsze+_rs req_i_ed by the

Beat Transfer Option. After these v_lues •re 8ivan, _.Vi_D set_ the _" [ temperature, vall emissivity, and continuation option. 5qV_MTD lets the user specify whether he wants Rar_fled flow and virt_•l origin options. 5q_MTD checks if

the rarefied flow option was selected. Rarefied flow cannot be used by H_at

Transfer Optio_ Z, _, "., 7, 9, 10, or 11.

m

p

3._1 SUBROL-"I D4E HTM£.'i.T

Subroutine HTMULT i.s called by .KAnt or MODIF'[ if s E.•t Transfer Multiplication factor i$ des_._ed. There ate 3 option types and HTMULT allows the _-sev

to de_ide if he wishes _o use each type. If option 1 i_ chosen, • L_i_zf •."-d

Turbulent t'actoz mast be soppli_d. If optic.n 2 is chosen, the somber ot times

must be _upplted. For each time a Lwnir_ez _nd turbulent m_itipii-: must be sup--

plied. If option 3 is selected, the number of Much n_m_ers mast be supplied.

For e_ch Nnch nmn_er,, _ L_inar and t_rbalent multiplier mutt _,e suppzzed.

HT_ULT converts these last ,,_ltiplicrs to lo$ values. For _pti_,zs 2 san 3,

there must be a minimum of 2 and a m_zimu_ of I0 entries.

_.12 SUBROUTL'_ TRANS

Subroutine TR_NS is called by MAiN or MODIFY to select the transition option to be used. TR_NS then requires the higBest and lo,es" values or r•t_o for

24
the tlansltion region depending on the o_tion _elected.

3 .I_ _BRO[T KNeE CROSS

Subroutin_ CROSS is called by K4_ or MODIFY' _ a Cross Flow s82_s_me._t is

r_eeded. _OSS selects the fr: ss Flow ad:'.stment cp_i_n t._ be used and Lsks

for data depending _n-hich _ticn is _elet_t_,

3.1 4 $_BROFTL'NE _O_

Subroutine FLOW -_s ._al!e_ _y _,A[N o_ MODIFY to set th_ flowfield and local

pressure options, /'he Pars=clef ID is passed throuih the subroutine cat1. If

ID_i then FLOW will create a new set of flowfield data. If II)=2 th-n FLOW modifies su old set of flowfield data. If ID=2 then the flowfield data must be

transferred fro_ the W array to the flowfield and "ocal pressure arrays. FF is

the flowfield option array. FFA is the array containing the angles correspondin s to the flowfield option. P is the local pressure option array, PA is the

1tray containin_ the angles correspond, ng to tt.e local l:,resaure option. Once

c_=vcrted, FI O_ ecbos the palrs of flowfield _nd local p_¢ssuze options _,i*h option sbreviations and corresponding angles, If no change _ are desired, then

FLO_ is exited. Otherwise, -"LOW _rcvides a table of flowfteld and local presau._e o_.tions with option numbers. T'ne user must select options by pairs with

corresponding angles. Choosing option -I. fo_ the flowfie!d option and the

local pressure option signifies that no more options are _o be included, If the

CP vs. ;_ach number table pressure option is chosen, FLOW requires a filename

co_tainin8 _he table, or the nua_er of table entrees, an_ M<_ and CP for each

entry. The format for the CP vs. _l_ch number file is an I3 on line one for the

number of _ch numbers. ]'he remaining lines contain the Mach number and the

pressure coefficient using a ZF_0.6 format. After a; 1 options _re selected,

FLO_ echos the pairs of options. If the options are correct, the rio. field and

_5
local pressuxe arrays are converted to the W array. FNAM5 is the variable for

the fileuame of the pressure coefficient vs Mach number table.

3.15 S_BROUTINE TI_EOM

Subroutine T_EOM is called by _AL_ or _.ODIFY if time dependent Geometry is

needed. Firet, the nun_ber of time dependent entries is set. Then the time, radius, lendth, and slepe or _weep angl are required for each entry.

!

3.16 SL-BRO_T L_E CONSUL

Subroutine CON°I_L is called by _tAIN or MODIFY to set the LAN_tIN control

flags. CONTRL sets the body point number for the use, the print option, output

units option, and the program input control parameters for the case. CONTRL

asks if LA.NNIN will create an output file and if the current case is the first

of a set of streamline cases. If the case is the first of a set of streamline

cases subroutine STR_ is called.

_.17 SUBROUTINE UNITS

Subroutine UNITS is called by MAIN to copy the working W array lntr lhe

output _ array. If MFLAG=I, then metric units are required and UNITS converts

the _ array into Metric units.

_.18 SUBROUTINE STRF_

Subroutine STREAM is called by CONTRL if s set of streamline cases is to be

created. If a streamline file is created by STRF_, it will be used by OUTPUT.

STREAM first checks if the time dependent geometry option was selected. If

it was, then streamline cases can not he used and STREAN returns control to

CONTRL. If time dependent geometry was mot used, then STREA)4 opens a temporazy

26

L :._ D
file to store the data for the streamline cases. Next, STREAN determines the

shock and local pressure options to be used by the streamline cases frol the

previous case. STREA)I then requires X distance, shock angle, body angle, and

body point n_be-, for each streamline case. STRE_ writes these values and the

'W' number that these values are to be stored in to the streamline file. The

parallel shock and Prandt-Meyer pressure options don't require both the shock

and body angles to be input. A negative value of X indicates the end of the

streamline cases.

The variables used by STREAM are:

I - X distance

SA - Shock angle

BA - Body angle

BP - Body point number

CASE - Case number

XPRT - Program input control parameter

21

J2

J3

J4

J5

J6

Jg

- 'W' index for CASE

- 'W' index for g

- 'W' index for SA

- eW' index for BA

- ewe index for BP

- eW' index for XPRT

- Flag used to mark parallel shock or Prandt-Meyer cases.

3.1 9 SUBROUTINE OUTPUT

Subroutine OUTPUT is called by MAIN to write the 'W' array values for a

case to the output file. FNA.q4 is _he variable for the filename of the output

file. OUTPUT opens this file unless previously opened. Next OUTPUT writes the

data for the current case to the output file according to the program input control parameter of the previous caJe. OUTPUT wri'es to the file the t_tle, timing par_eters, and pxint control, the number of time dependent trajectory table

entries, the trajectory data, an_ the case data. The last W of the case data to

be written to the file is the program input control parameter. OUTPUT checks to

see if the case just written is the first of a set of streamline cases. ISTIL_I

indicates streamline cases. If streamline cases are indicated, then OUTPUT co27

m
pies the streamline cases to the OUTI_T _ile from the temporary streamline file.

After the last streamline case is written to the OUTPUT file, OUTPUT sets the

prograz input control parameter for the last streamline case. OUTVET then

closes and deletes the temporary streamline file and returns to MALN.

28
!

I

l,-.-

J

OF POOR QUALrFY

)-

io

29

E

I.,..

lid

0

0

I,,.

U

Z

P

d,

I,L
Section 4.0

OErTI_ T DESCRIPTION

T_.e printed output fr:,,_ LA.NM_N comes in two forms. Tr, e detailed printout

for each time point is give_, if JFOQ = 0 or l. This detailed printout ccrtaJns

the variables listed in Table 4.]. The definitions mud u_it5 are g._ven in TaSle

4.1 for each of the variables printed.

If the s_ary printcut is selected (i.e. JFOG = I or 2) the ._utput contains the variables shown in Table 4.2. This table contains , listing of _,,elve

time dependent variables for each body point. The varisole and units are clearly labeled on the output. The a_mmary page can bo obtain*d for two sets of output units. If W(648) = 0 the output is in Enllish units and if W(648) - I the

output is in Metric units as lustratcd in Table 4,2.

An output, tape or fil_, can be created from LAN_4_ if I(643) " 1.0. The

output file is a card image of the printed summary pa_e.

3O
i

VARIABLE

Table 4.1

_DIATE P_LN"r OUTleT P_tRAMETERS

DEF IN IT ION _NITS

D

TI.F_

ZINF

VL-N7

ALN"F

V'E

RE L--',_

MINF

M'U

ME

L

PR

EMS*F

PINT

PE

PT

ALFRA

CF/2

TAU •

TINF

TU

TE

1"I"

T*

1"X

TW

H I_F

HU

RE

lit

H*

_R

HW

PHI

RHOI

RHOU

RBOE

RI]OT

kliO*

RItOR

RBOW

TIME

ALI ITUDE

FitEES T_._ VELOCITY

FREESTR.EAM SPEED OF SOUND

EDGE _,q_LOCITY

FREESTREA._t REYNOLDS ._./FT

FREESTR_&_ ! _.'_OLDS NO.

FREESTREAM MACIt NO.

UPS_ MAClt NO.

EDGE MAC_ NO.

RUNNING LI_GTE

NOSE RADIUS

_ANDTL NUMBER

EMISSIVITY * VIEW FACTOR

FREEST_ PRESSURE

UPSTI_ PRESSURE

EDGE l_ES SURE

POST SHOCK TOTAL PILESSU1LE

LOCAL ANGLE OF ATTACK

LOCAL SXIN FRICTION COEF./2

WALL SHEAR FORCE

FREESTREAM TEM_RA1X_RE

UPSTkE_ TEMPERAa_'RE

EDGE TE _ERATL'RE

POST SBOCK TOTAL TEMPERATURE

ECKERT REFERENCE TEMPERATURE

pp REFERENCE TEKPERATURE

WALL TEKPERATURE

FREES_ STATIC ENT]tALPY

UPSTRE_ STATIC ENq'iIALPY

EDGE STATIC I_'THALPY

TOTAL ENTIIALPY

ECKERT REFERENCE ENTIIALPY

Pl_ REFEILENCEENTItALPY

WALL ElqTBAL l_f

SWEEP &_GI_

FREESTREAM DENSITY

UPSTREAM DENSITY

EDGE DENSrl_

POST SROCK TOTAL D_SITY

ECKERT REFERENCE DENSITY

pp REFER.I_CE D_SFFY

WALL DLNSITY

31

(SEe)

(FT)

(F'I-/SEC)

(FT/SEC)

(FT/SEC)

(1/FT)

( -- )

(--)

( -- )

( -- )

(F-r)

(FT)

( -- )

( -- )

(I_F/SFT)

(LBF/SFT)

(T..BF/SFT)

(LBF/SFT)

(DF.L;)

(--)

(I..BF / SFT)

(F)

(F)

(F)

(F)

(F)

(F)

(F)

(BT171I..B_4)

(BTUtLBM)

(BTC/LBM)

(BTV/L.BM)

(B'I_/t.BM)

(B'I_ / I..BM)

(BT_/LBM)

(DF=_)

(SLIX;/CFT)

(SL_ICFT)

(SLU_i CFT)

( SLI:K;ICFT)

(SLUG/C_)

(SLOG/CFI)

( SLUG/ CFT )
PARA_

MI] INT

WF U

M'U E

M_ T

MV *

MT R

MT W

-"kF_k2

NC L

NC T

KILECOV L

tEE COV T

I_SUB L2

KSVB

KSUB L3

KSCB T3

KSFB L

KS['B T

PARA

PCTT

NSt'B C

B IDEAL

B RECOV

T RECOV

OCONV

OCI_TAL

OC C'W

OC C'WT

LAMLNAR TRANSITION PA.RA__.R

F'R_S ,r_ "vISCOs IT_

FPSTREA._( _,ISCOS I_

EDGE v!SCO5 I_

POSTSdOCK TOT._L VISCOSFI'_

ECKERT R.EFERL'NCE VISCOSITY

pv RZFER._CE VISCOSFF_

tALL VISCOSITY

T'_,3C_U:.ENT T_N SIT I0_ PAR_V_TER

FLO_FIELD FLA] NT._ER

ANGLE FOR CORRESPONDING FLAG

LGMINAR HEaT TIt_NS:-=ER COEFFICIENT

"IWR.BU'LENT HEAT TRANSFER CX)EFF ICIENT

I.,_L'NAR RECOVERY E'CTRALPY

TVRBVL_T RECOVERY E4TtL_L, PY

LA.MLNAR HEATING RATE

T[TRB_'N'T EEATING RATE

LA.ML-NAR TIME DEPL'ND_T M_LTIPLIER

TURBULENT TIME DEP_'DKNT MULTIPLIER

LAMINAR EAC_ ,NO. DEPENDKNT MELTIPLIER

"I'URB_T KACB NO. DEPtLNbE_I MrLTIPLIER

TOTAL LAMINAR MVLTIPLIER

TOTAL TYRBULKNT _LTIPLIER

TRANSITION PAIL_METER VALVE

PERCE_,'T TUF_,_'I" BEATLNG / 100

BEAT TRANSFER COEFFICIENT

IDEAL GAS A IR HEAT TRAN St ER COEFF I C IENT

RE LX)VERY KNTEAL PY

RECOVERY TEMPERATVRE

tEATLNG RATE BASED ON B_

I{EATING LOAD FOR T_

IFALL RADIATION RATE AT T)

WALL RADIATION LOAD AT T_

NET KEATING RATE (QCONV-C_R)

NET BEATING LOAD

RADIATION E_VILI_RII]M _ALL TEMPERATVRE

COLD WALL KEATLNG RATE (Tt - 0)

COLD _ALL KEAIL_G LOAD

32

I._F-SEC / SFT

LBF-SEC/SFT

L_F-SEC / SFT

L_,F-SEC.' SFT

L_F- SEC / SF-_F

LBF- SEC,' SFT

!._F-SEC, SI-q

(DF.6)

(L,BP. ' SFq-- S}-C

(I.,B_ / SFT- CEC

(BT'C/LB_)

(t_TV_i LB_)

(B'I_/SFT- SEC)

(BTU/SFT- SEC)

( _ )

( _ )

( _ )

(L_/SFq- SEC)

_BT[/B_- SFT-R)

(F)

( B'i_/S_ l-_F.c)

(B'r_lSFT)

( B'FI3/ SFT- SEC )

(B'r!3 / SFT)

(BT_/SFT- SEC)

(B'r_l SFT)

(F)

(BT_I SF'T- SEC )

(lri_ / SF'T)
t--

• _

Z

_ .._ . :_, ._ ._ .

?_..===.• ,=_.-;°.==-.=. •

_,-_ _ _ _ _t _ _,_

_ _ _ _ fJ_ _T_j •

• • • • • • • • • • • •

E

X

b 3.

_r

..a

01"

m

, 4

7 "

._ _r

1-

• . ° • ° _ ° • • • , , _

; ! I ! I ! i _ _ I ! : g

• • • • • • • • • • • • •

-._ ....... _ "-

33
W ARRAY DESCRIPTION
r

APPENDIX ^

W ARRAY DESCRIFTION

ARRAY/SYMBOL, VAR IABL _L_ IT ION

W<I -

W#2 =

W(3 -

I(4 =

W(_) =

W(6) =

V(7) =

W(8) =

W(9) =

V(IO) -

W(II

W(12) =

W(13 -

W(24) =

W(15) =

W(16) =

e(17) =

W(18) =

W(19) -

l(20) -

W(21) =

W(22) -

W(23) -

_[24) -

T! = tl

DT-I - _tl

T2 - t2

aT2 = at2

T3 = t3

DT3 = At3

T4 -- t4

(first _. -u!at!cn time, :ime I)

"de:'_a .'.ime s_e; be'.,ee: time :I end *.27

(:/me 2

(delta time _tep between and t3

(time 3

(delta time step between t3 and t4)

(time 4)

DTCALC (KCALC calculation interval factor)

(Open Location)

ATFLAG (atmospheric freestreem properties option flag)

(NI_LAG ,, heat _ransfer method option flag)

RN = RN(nose radius or local cylinder radius, leading edge

radius, ft.)

EL (running length, ft.)

PARA! (transition data)

_'L (2nd po, er of Mangler transfc, rmatlon factor for lazimr flow)

K'_q" (fifth power of Mangler tra_-sformatloa factor for turbulent flow)

l_II (sweep angle, _,., local slope, 5, deg.)

AKL _ (constant laminar multiplication factors)

AI2 = (constant tarbulent multiplication factorb)

PARA2 (transition data)

Windward B'..ttom Centerline Fall Enthalpy (Btu/ibm)

Flap Length (f_) for heat transfer option 10

U " EMIS (emilsivity) 0): If (_M,S.LE.0)EMIS=0.8

0

TIN (initial temperataxe, F)

A-1
l(25) -

l(26) -

w(27) =

w(28) -

v(29) =

Fin Length to Point of interest for Heat Transfer Option 11 (it)

Fin Angle at a = _ = 0 for Heat Transfer Option 11 (Des)

TRFLAG (trant_tlon criteria option flag)

ELFAC (transition zone length ratio)

_9_LFLG (virtual origin option)

W(30) = Fin Option Flag 0 = Fin angle

I = a + Fin angle

2 = _ + Fin angle

GF(1) = FF(1)--

GF(2) _ FF(2)

GF(3) = FF(3)

GF(4) = FF(4)

GF(5) = FF(5)

w(31) =

W(_2) =

W(33) =

W(34) =

W(35) -

W(36) = GF(6) = FF(6)--

_> Flowfteld and local pressure option flags

W(37) = BLFA(1) (ALFA(1) = BLFA(1) + ATAK) degree

BLFA(2) (ALFA(2) - HLFA(2) + ATAX) degree

BLFA(3) = ALFA(3) degree (add AT_ to ALFA if W(263) = 3.)

BLFA(4) = ALFA(4) degree (add ATAK to ALFA if W(264) = 4.)

BLFA(5) = ALFA(5: degree (add ATAX to ALFA if W(265) = 5.)

BLFA(6) = ALFA(6) degree (add ATAK to ALFA if W(266) = _.)

BLFA(7) - ALFA(7) degree (add ATAX tc ALFA if W(267) - 7.)

BLFA(8) = ALFA(8) degree (add ATAX te ALFA if W(268) = 8.)

BLFA(9) = ALFA(9) degree (add ATAE to ALFA if W(269) = 9.)

m_(1) - FF(7)--

I

!t8(2) = FF(8) -->

I

1111(3) - W(9)--

(Open Locat_os)

Flowfield and local press_Jre option flags

ENT_ (number of t2ajectory points)

W(38) =

W(39) =

W(40) =

W(41) =

W(42) =

W(49) -

W(44) =

W(45) =

W(46) =

W(47) =

W(48) =

W(49) =

W(50) =

A-2
W(51) = I"Z(1)

Q

W(IO0)= "I:Z<._O)

I

-->

I

(Trajectory Time. aec)

W(101)- ZZ(1)

. I

• I

W(150)- ZZ(50)

(Trajectory _ltitude, feet)

I(15!)= VZ(1)

• I

. I

I(200)= V'Z(50)

(Trajec=ory V:lec!ty, ft/sec)

W(201)= CFFLG (croaaflow option flag)

W(202)= DSU_O (crossflow rectangular width, D , ft)

o

_(203)= _L.MBDA (delta .ing sweep anglo, k (deg))

W(204)= UDOT (real gas velocity gradient correction factor, U)

W(205)- CORN'R (rectangle corner radius, R (ft))

c

W(206)-

• I

• i

W(208)-

--> (Open Locations)

T(209)= CON'FLG (continuity option)

V(210)= (Open Location)

W(211)- Al(1)-

W(260)= A1($0)

I

--> (Trajectory positive a, degree)

I

W(261) = 1.---

I

W(262)- 2. I

Built into aef f

p:ogram neff

added to W(37):

If (_(261).LE.0)1(261)=1.0

added to W(3g):

If (W(262).LE.0)W(262)=2.0

- "z. ..alp

A-3
Ib

m.

_'(263)--

w(264) =

_(265)=

W(266 =

W(267 =

268:'=

w ';_) =-

W(27C) =

W(313)=

3 .---- Values c_

l off

4, l must be a

I elf

5. I input for aef f

!

E. --_ tc, be aef f

I

?. I added to,

i aeff

8. } bo_y

I aeff

9.- .... angl_ aeff

added to W¢_9)

•dded to W(_O)

added tc W(41 _,

added tc W,',42)

adJed t_ W a3>

added to, Wi_4)

added to Wia._}

I

---_,(Open Locations_

I

W(314)= .N_CS (raref,ed flag 0 - _harp cone option used

1 - flat plate option used)

W(315)= k_LE%....,u_svc iation fla g 0 - Lewis number = 1.4

1 - L,e_is number = 1.0)

W(316)= Q<SU_ (Imtegrsted ccm'ective heat flux, Btu/sq ft)

_' 317)= (Open L?cation)

W:318)= ,:Open Locatior)

W_319)= RA,%77uG (skit. friction I Karman Reynolds a:,olcgy used)

(Flag 0 Colburn's equation used)

W(320)= K%_'T2 (n_mber of multipliers read in as fr_tzticn of time)

Limit I0

_(321)= TKI(1)-----

• i

• I

W(330)= TKI (i0)--

(Table of multiplier t:=es, sec)

W(331)-- AXL2(1)----

. I

• ---->

• i

W(340)= A.E[,2 ( 1 O) ----

(Table of laminar multiplier fac':ors)

A-_
V(341),. kl'T2 ( 1)--

. I

I(350)= AKT2 (I0) _-

I

(Table of turbulent multiplier factors)

W(351)=

. I

• !

wC353)=

(Open Locations)

W(3S4)= ]JUNC (surface distance to start of turbulent boundary layer, ft)

W(355)=

W(3_9)=

W(3601=

W(3gl)-

V(3701=

W(3711=

W(380)=

W(3811=

Q

W(390)=

I

_> (Open Locations)

I

EI_M3 (number of Mach dependent multipliers)

TMACH(1)

I

--> (Logl O) (M_ )

I

"1"_C_ (10) _

/fiG.3 (1)"

I

_> (L°gl0 hi/hu)laminJr multiplier

I

AKL3(10)

AKT3(1)

I

--> (L°810 hi/hu)turbulent multiplier

I

AKT3 _i0)

I

_) (Open Locations)

. I

W(39_)=

V(400)= ENALT'Z (Table of wind tunnel fzeestream properties, limit 50)

W(401)= FSALT (1)._

• i

• I

N(450)= FSALT(50) _

-_> (Table of aititude data, ft)

A-5
4_

J

_(451)- FSTE_(1)_

o

W(500)- FSTE_(50)_

I

_> (_able of wind tunnel freestream temperatures,

I R)

V(501)= FSPRES (1)--

• I

• l

W(550)= FSPR._ (50)_

----> (Table of wind tunnel freestream pressure,

lb/sq ft)

W(551) -=

. I

. I

W(5_9)=

_> (Open I, ocs tions)

N(560)= ]_T3 (Number of Table Entries for Geometry as Function of T_me)

W(_61)- .TILL(1)

. I

. I

W(570)= I"WZ(10)_

_-) (Body Geometry is Varying with T_me, Sec)

W(571)- LNZ(1)

• I

• I

W(S80)= L_z (I0)--

_) (N, se _adius, Ft)

W(581)= ELZ(1)

• i

o

• I

W(590)= EI.,Z (10) _

-_> (Ru_ning Length, Ft)

W(591)= I'BIZ(1)_

W(600)_ PIll2 (I0)_

I

_) (Local Slope or _weep ._ngle, Degree)

!

I(601)-

W(610)=

I

_) (Open Locations)

I

I(611),, Body Point N_mbe_

A-_
W(612)-

I

W(640)=

W(641)=

W(642)=

W(643)=

W(644)=

W(645)-

W(646)=

W(647)-

I(648)=

W(649)=

_> (Open Locations)

.'F_ (Input Control Fla|)

J-Fq,_ (Print Option)

Output File from VANOUT

(Open Location)

3"FGO (Initialization Opt 4on)

NO, CON (Rarefied Flow Option)

(Case Number)

Output Units Option, O.-English, l.-getric

_FCP (Pressure Coefficient Input Option)

I(650)= NSB (Cone Flow Option for Rarefied Flow)

W(651)=

• I

• _> (YAW &ngle _, degree)

• I

W(700)-

A-7
APPENDIX B

SA._tPLE CASES
APPENDIX B

SA.RH.. E CASES

Two sample cases are presented in this appendix which ,tercise both the

P_EMIN and LANMIN code_. The components shown here follow those depicted in

Fi$. 1.1.

_eatina Indicator Sample Case

The input for a heating indicator run is rather straight-forward using PREMIN. After the execution command, units selection, and printout selection, the

trajectory is input. PR_IN then displays the trajectory data twenty lines at a

time waiting for a carriage return before displaying the next twenty. After the

trajectory is input, the atmospheric option is chosen. The preceeding steps are

standard in most input. If the heating indicator option is selected, the remaining input is much simpler than for most other options. During execution of

PRENIN, if the answer to a question it an end of file character, then PRENIN

will stop execution. If the answer to a question is incompatible with the readin S format, then the question will be _easked until an acceptable answer is received.

The PRF_tIN interactive input is fcllow_'d by a listing of the input trajectory file. The first line of the trajectory file contains the title. The

second line contains a Beta flag end the number of trajectory table entries.

The third line through the end of the file contains the trajectory data. Each

line of trajectory data contains a time, altitude, velocity, angle of attack,

and, if the Beta flag equals one, the yaw angle. A listing of the PRF_IN output

file follows the trajectory file. The LAN_IN output listing is given last. The

summary output is labeled with units and is self exp]anatory.

B-1
PREMIN INTERACTIVE RUN

HEATING INDICATOR CASE

RdN PREMIN

INTERACTIVE I*_UT TO LAPC _,';r,,IVER - LANMIN

OUTPUT F L E METWOD

.

2.

CREATE A NEW OUTPUT FILE

MODIFY AN EXISTING OUTPUT FILE

oFq', iON SELECTED ?

1

DO YOU WANT TO INPUT DATA IN ENGL t SM OR METRIC ?

E_LISH

INTERACTIVE INPUT FOR CASE I

SPECIFY PRINTOUT INTERVALS

INITIAL TIME (SEC)

0.0

PRINTOUT INTERVAL I (SEC)

25.0

SEOOND TIME (SEC)

500.0

PRINTOUT INTERVAL 2 (SEC)

14.0

THIRD TIME (SEC)

1200.0

PRINTOUT INTERVAL 3 (SEC)

29.0

FOURTH TIME (SEC)

1925.3

ARE THE PRINTOUT TIMES CORRECT ?

Y

DELTA TIME

DELTA TIP_

DELTA TIME

B-2
TRAJECTORY INPUT

DO YOU HAVE

YES

WHAT IS THE

REENTRY.TRJ

A TRAJECTORY

FILE NAME ?

INPUT FILE ?

TIME

(SEC)

ALTITUDE

(FT,)

VELOCITY

(FT/SEC)

OF POOR QUALITY

ANGLE ATTACK

(DEG)

I O.3000E+O0 0.3963E+06 0.2457E+05 0.4113E*02

2 0.4530E+02 0.3738E-06 0.2459E+05 0.4126E+02

3 0.9030E+02 0.3515E+06 0.2462E*05 0.4!21E+02

4 0.1353E+03 0.3295E÷06 0.2464E+05 0.4046E+02

5 0.1803E,03 0.3080E+06 0.2466E+05 0.4065E+02

6 0.2253E+03 0.2880E+06 0.2465E+05 0.4190E+02

7 0.2703E+03 0.2697E+06 0.2461E+05 0.3939E+02

8 0.3153E,03 0.2563E+06 0.2447E+05 0.4071E+02

9 0.3603E+03 0.2502E+06 0.2422E+05 0.4174E+02

10 0.4053E+03 0.2470E+06 0.2392E+05 0.3995E+02

11 0.4503E+03 0.2446E+06 0.2361E+05 0.3928E+02

12 0.4953E+03 0.2425E+06 0.2328E+05 0.3966E+02

13 0.5453E+03 0.2400E+06 0.2288E+05 0.3907E+02

14 0.5693E+03 0.2388E+06 0.2268E+05 0.3932E+02

15 0.5933E+03 0.2377E+06 0.2247E+05 0.3902E+02

16 0.6173E+03 0.2366E+06 0.2225E+05 0.3925E+02

17 0.6413E+03 0.2353E+06 0.2202E+05 0.3948E+02

18 0.6653E+03 0.2337E+06 0.2178E+05 0.3997E+02

19 0.6893E+03 0.2320E+06 0.2153E+05 0.4001E+02

20 0.7133E+03 0.2323E+06 0.2126E+05 0.4025E+02

TIME

(SEC)

ALTITUDE

(FT)

VELOCITY ANGLE ATTACK

(FT/SEC) (DEG)

21 0.7373E-03 0.2303E*06 0.2098E*05 0.4046E+02

22 0.7613E+03 0.2279E+06 0.2068E+05 0.4014E+02

23 0.7853E+03 0.2252E+06 0.2036E+05 0.4016E+02

24 0.8093E+33 0.2223E+06 0.2002E+05 0.4016E÷02

25 0.8333E+03 0.2190E+06 0.1965E+05 0.4027E+02

26 0.8573E+03 0.2153E+06 0.1924E+05 0.4040E+02

27 0.8813E,03 0.2114E+06 0.1879E+05 0.4012E+02

28 0.9053E+03 0.2076E+06 0.1830E+05 0.4030E+02

29 0.9293E+03 0.2056E+06 0.1776E+05 0.4001E+02

30 0.9533E+03 0.2025E+06 0.1718E+05 0.4200E+02

31 0.9773E+03 0.1972E+06 0.1654E+05 0.4090E*02

32 0.1001E+04 0.1922E+06 0.1587E+05 0.4075E+02

33 0.1025E+04 0.1872E+06 0.1513E+05 0.3987E+02

34 0.1049E+04 0.1826E+06 0.1435E+05 0.3943E+02

35 0.I073E+04 0.1796E+06 0.1357E+05 0.3953E+02

36 0.I097E+04 0.1766E+06 0.1279E+05 0.3975E+02

37 0.1121E+04 0.1725E+06 0.1201E÷05 0.3896E+02

38 0.1145E+04 0.1675E+06 0.1122E+05 0.3812E+02

39 0.116£E+04 0.1619E+06 0.I044E+05 0.3697E+02

40 0.;240E+04 0.1500E+06 0.8336E÷04 0.3407E+02

B-3
TIME _TITUDE VELOCITY ANGLE ATTACK

(SEC) (FT) (FT/SEC) (DEG)

41 0.1302E+04 0.1339E+06 0.6757E*04 0.2820E+02

42 0.1364E+04 0.1174E+06 0.53a2E+04 0.2305E+02

r.3 0.!426E+04 0.i062E+06 0.4064E+04 0.2027E*02

_.4 0.1488E+04 0.891 E+05 0.2917E+04 0.1647E÷02

45 0.1550E+04 0.7635E÷05 0.1 915E+04 0.1055E'_02

46 0.1612E÷04 0.5744E+05 0.1!51E+04 0.77gCE#9!

47 0°!674E+04 0.4167E_-05 0.8009E+03 0 o772_E"-S I

2,6_.+_J 0.6 OE+03 O. 7_OE_':l

49 0._860E+04 0.3337E"Oz: 0.5120E+C3 0.37_3E_':1

50 0.1925E+04 -0.3000E+01 0.2020E+03 -0.122DE*01

DO YOU WISH TO G!ANGE ANY OF THE TRAJECTORY INPUT ?

NO

DO YOU WISH TO WRITE T_IS INPUT TO A FILE ?

NO

TRAJECTORY INPUT IS COMPLETE

AT_K)SPH ERE D#"

OI:'TIONS 1. 1962 U.S. STAND#_RD A'MOSF_wERE

2. WIND TUNNEL OFq ION

3. INPUT ATMOSPHERIC DATA(ALT, T-INF,P-!NF)

4. 1_3 PATRICK AIR FCRCE BASE ATMOSPHERE

5. 1971 VANDENBERG REFERENCE A_OSt:h'-IERE

OPTION S_LEC'TED ?

4

1963 PATRICK AIR FORCE BASE ATMCSF:_-IERE

IS _IS o;:qFION CORRECT ?

YES

DO YOU WANT TO RUN A HEATING INDICATOR ?

YES

HEATING INDICATOR

FAY AND RIDDELL

RADIUS = I FT SI:_-IERE

WALL TEMP : 0 DEG. F

LEWIS NK:). = 1.0

SUMMARY PRINT ONLY
CON,TIROL FLAGS

YOU ARE COMPLETING INPUT FOR CASE I

WHAT IS THE BODY POINT NUMBER FOR CASE I ?

!001

SHOULD LAM_!N CREATE AN OUTPUT FILE FOR CASE

YES

I ?

OUTPUT UNITS OPTIONS

O. ENGLISH

I. MET_ IC

OPT ION SEL ECTTED ?

O.

IS CASE

AS CASE

NO

2 ALONG THE SA,vE STREA_I_ INE

I ?

INF:_jT (_3NTI_OL FL AG

•

2.

3.

4.

5.

6.

NEW CASE FOLLOWS USING TiTLE,TIMING AND TRAJ.

DATA FROM PREVIOUS CASE

END OF INPUT (LAST CASE)

NEW CASE FOLLOWS USING "I-RAJ.DATA FROM F_REVIOUS CASE.

NEW TITLE AND TIMING. INITIAL CASE DATA UNCHANGED.

NEW CASE FOLLOWS USING NEW TITLE,TIMING,TRAJ. AND CASE DATA.

(INITIALLY ZERO W ARRAY)

SA#IE AS (I) EXCEPT ZERO ALL CASE DATA FROM PREV_3US CASE

SAME AS (3) EXCEPT INITIALIZE ZERO ALL TIMING AND CASE DATA

OPTION SELECTFED ?

2.

***** INFUT OOMPLETE FOR CASE 1  _

DO YOU WANT TO MAKE ANY MODIFICATIONS TO CASE

NO

1 ?

B-5
CREATE OUTPUT FiLE

_AT IS THE N&ME OF T-_E _)STPUT FiLE TO BE C£EATED ?

OUT_UT.F IL

W_AT IS THE TiTL _. F_ CASE I 7 _NCTE: 72 _&-_. _ vIT)

S_-S-I _EE,; "_ v T_j, #^.._i_-_-_ m_ p_ .....

** *****'_ Ob!T>UT FIL _-_C_v_, ,_PT___ ********

>

m

B-6
TRAJECTORY FILE LISTING

HEATING INDICATOR CASE

ORIGINAL PAGE _

OF POOR QUALITY

STS-I REENTRY TRAJ.

0 50.00000

0.3000E+O0

0.4530E+02

0.9030E+02

0,1353E+03

0.1803E+03

0.2253F+¢3

0.2703E+03

0.3153E+03

0.3603E+03

0.4053E+03

0.4503E+03

0.4953E+03

0.5453E+03

0.5693E+03

0.5933E+03

0.6173E+03

0.6413E+03

0,6653E+03

0.6893E+03

0.7133E+03

0.7373E+03

0.7613E+03

0.7853E+03

0.8093E+03

0.8333E+03

O.B573E+03

0.8813E+03

0.9053E+03

0.9293E+03

0.9533E÷03

0.9773E+03

0.I001E+04

0.I025E_04

O. I049E+04

0 .I073E+04

0 .I097E+04

0.I 121E+04

0.1145E+04

0.1169E+04

0.1 240E+04

0.13 _2E+04

0.1364E+04

0.1426E+04

0.1488E+04

0.1550E+04

0.1612E+04

0.1674E+04

0.1736E+04

0.1860E+04

0.1925E+04

(OR£_TER)

0.3963E+06

0.3738E+06

0.3515E+06

0.3295E_06

0.3080E+06

0.2880E+06

0.2697E+06

0.2563E+06

0.2502E+06

0.2470E+06

0.2446E+06

0.2425E+06

0.2400E+06

0.2388E+06

0.2377E+06

0.2366E+06

0.2353E+06

0.2337E+06

0,2320E+06

0.2323E+06

0.2303E÷06

0,2279E+06

0.2252E+06

0,2223E+06

0.2190E+06

0,2153E+06

0.2114E+06

0.2076E+06

0.2056E+06

0.2025E*06

0.1972E+06

0.1922E+06

0.1 872E+06

O. 1826E+06

0.17 96E+06

0.1766E+06

0.1725E+06

0.1675E+06

0.1619E+06

0,1500E+06

0.1339E÷06

0.1174E+06

0.1062E+06

0.8910E+05

0.7635E+05

0.5744F+05

0.4167E+05

0.2760E+05

0,3337E+04

-0.3000E+01

0,2457E+05

0.2459E+05

0.2462E+05

0.2464E+05

0,2466E+05

0.2466E,05

0.2461E+05

0,2447E+05

0.2422E+05

0.2392E+05

0.2361E*C_

0.2328E+05

0.2288E+05

0.2268E+05

0.2247E+05

0.2225E+05

0.2202E÷05

0.2178E+05

0.2153E+05

0.2126E+05

0.2098E+05

0.2068E+05

0.2036E+09

0.2002E+05

0.1965E+09

0.1924E+05

0.1879E÷05

0.1830E+05

0.1776E+05

0.1718E÷05

0.1654E+05

0.158_+05

0,1513E+05

0.1435E+05

0.1357E+05

0.1 279E+05

O.1201 E+05

0.1122E+05

0.I044E+05

0.8336E+04

0.6757E+04

0.5342E+04

0.4064E+04

0,2917E+04

O. 1915E+04

0.1151E+04

0.8000E+03

06810E+03

0.5120E+03

0.2020E+03

B-7

0.4113E+02

0.4126E÷02

0.4121E+02

0.4046E+02

0.4065E+02

0.4190E+02

0.3939E+02

0.4071E+02

0.4!74E+02

0.3995E+02

0.3928E+02

0.3c:_6E+02

0.3907E+02

0.3932E+02

0.3902E+02

0.3925E+02

0o3948E+02

0,3997E+02

0.4001E+02

0.4025E+02

0.4046E+02

0o4014E+02

0.4016E+02

0.4016E+02

0.4027E+02

0.4040E+02

0o4012E+02

0.4030E+02

O.4_ulE+02

0.4200E*02

0.4090E+02

0,4075E+02

0.3987E+02

0,3943E+02

0,3953E+02

0.3975E+02

0,3896E+02

0.381 2E+02

0.3697E-,02

0.3407E+02

0.2820E+02

0.2305E+02

0.2027E+02

O. 1647E+02

0.1086E+02

0.7790E+01

0.7720E+01

0.7090E+01

0.3780E+01

-0.1220E+01
PREMtN OUTPUT FILE

HEATING INDICATOR CASE

Uk:u,l:_r_L :, _', .

OF POOR QL#_:.,_,

STS-1 REENTRY TRAJ. (C_I"Eq) r_AFB RE_. #_S.

0.000 2_., J0

4.000 !200.900

925.300 .- J_

5O .000

3.%0 3 _3::.000

45.300 373800 .S!00

93.3 ''_'v,, 35_ 5. .v J,,

135.300 3295 _r,_. .vu_" _c,

80.300 3_8_0

225.300 288000.000

270.300 269700.000

315.300 255300.000

360.300 250200.000

405.300 247000.000

450.300 244600,000

495.300 242500.000

545.300 240000.000

569.300 238800.000

593.3 00 2377 00. 000

617.300 236600.000

641 .300 235300.000

665.300 233700.000

689.300 232000.000

713.500 232300.000

737.300 230300.000

76! .300 227900.000

785.300 225200.000

809.300 222300. ,rP_Jv

833.300 2! 9000.000

857.300 215300.090

88! .300 211400._#0

905.300 207600.000

929.500 205600.000

955.300 202500.000

977.300 197200.000

1001.000 192200.000

1025.000 187200.000

1049.0C0 182600.000

1073.000 179600.000

!097.000 176600.000

1121,000 172500.000

I 145.000 167500.000

1169.O00 161900.000

1 240.00C 150000.000

1302.000 133900.000

136_.000 117400.000

1426.000 I06200.000

1488,090 891 00.000

IND. CASE

29.000

24.57 O. O:,O 41 .13b 0.071.i

2 ".5 _:;. 050 4 _ . 26 0 O. O:J,i

24£20.C00 4! .2!0 0.00:

2 :.#,40.000 4_ .450 O .OOC

_'_._J0 _-S 650 O. _''-

24660.000 41 .900 0.030

24_,In.000 . 39.390 _. ,. O00

24470.090 40.7!0 2.92_

24220.000 41 .740 0.0::

23920.000 39.950 0.000

23610.000 39.280 0.000

23280.000 39.660 0.000

22880.000 39.070 0.000

22680.000 39.320 0.000

22470.000 39.020 0.000

22250.000 39.250 0.000

22020.000 39.480 0.000

21780.000 39.970 0.O00

2_530.000 40.010 0.O00

21 260.000 40.250 0.000

20980.000 40.460 0.000

20680.000 40.140 0.000

20350. 0_0v 40. I 60 0 _ _

20020.,nO,, 40.,_60 _._._m nnn

! 9650.000 40.270 r'.OOD

19240.000 40."J0 0.000

18790.000 4C.120 0.000

i8309.000 40.300 0.000

1776_.000 -_0.010 0.000

17180.000 42.000 0.000

16540.000 40.900 0.000

1 5870.000 40.750 0.000

15130.000 39.870 O.O00

14350.000 39.430 0.000

13570.000 39.530 0.000

I2790.000 39.750 0.000

I2010.000 38.960 0.000

11220.000 38.120 0.000

10440.000 36.970 0.000

8336._00 34.070 0.000

(5757.000 28.200 0.000

5342.000 23.050 0.000

4064.000 20.270 0.000

2917.000 16.470 0.000

B-8

I
ORIGINAL.

OF POOR

10

37

611

642

1550. 000

1612.000

!674o000

I"/36.000

1860.000

I925.000

4.0000 11

90.0000 38

1001.0

2.0000 643

. r",J,.,,.,, ,_, ",mv 12

90.0000 3!5

I.0000 647

76350.000

57440.000

41670.000

27600.000

333?.000

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].OOOC

1 .... '_n 64!

19!5,0CO 10.860 O.OC 3

11:51.000 7,790 0.000

800.000 7.720 Fj.O00

F,_: .0_ 7.090 v .,Ju_'

512 _rn 3.780 C.O00

202.000 -_.220 _ _'_"

!

B-9
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B-13
¢::_ E M -r" E C _--_ I r'-,J C.

Wind Tunnel Sa_____le Case

The example case given herein corresponds to the results presented in

Volume I Fig. 7.15 and 7.16 for X/L = 0.!, 0.2 and 0.3. The problem solved is

heating to the bottom centerline of an orbiter using the effective running

length concept. In the wind tunnel case, time is used to denote different run

conditions. Since the effective running length changes ,tth angle of attack and

angle of attack with rum conditions, the time dependent geometry option is used.

The PRE?4IN interactive listing is followed by the PP_MIN output file. The

output listing fro_ LkN._IN resulting from the PR_IN output file is given last.

The output lisiting contains the intermediate print as well as the summary page.

The description of the intermediate output symbols and units is given in Table

4.1. The s_ary print follows each case. Cases 1, 2, and 3 are for body

points 100, 200 and 300 corresponding to X/L = 0.10, 0.20, and 0.30 respectively. The heating load in the summ_ry print has no _eaning for a wind tunnel case

where time is a run number indicator.

B-14
INTERACTIVE PREMIN

WIND TUNNEL RUN CASE

i i i, I

RUN PREMIN

INTERACTIVE INPUT TO LARC MINIVER - LANMIN

OUTPUT FILE METHOD

1 •

2.

CREATE A NEW OUTPUT FILE

MODIFY AN EXIST NG OUTPUT FILE

OPTION SELECTED ?

I

DO YOU WANT TO INI::_jTDATA IN ENGLISH OR METRIC ?

ENGLISH

INTERACTIVE INPUT FOR CASE I

SPECIF'Y PRINTOUT INTERVALS

INITI_ TIME (SEC)

1.0

PRINTOUT INTERV_ 1 (SEC)

1.0

SE_ND TtME (SEC)

4.0

PRINTOUT INTERV_ 2 (SEC)

0.0

THIRD TI_ (SEC)

0.0

_INTOUT INTERV_ 3 (SEC)

0.0

FOURTH TIME (SEC)

0.0

ME _E _INTOUT TIMES _RRE_ ?

YES

bELTA TIME

DELTA T IME

DELTA TIME

B-15
TRAJECTORY INPUT

DO YOU HAVE A TI:_AjECTORY INPUT FILE ?

NO

WHAT IS 17_E NUI_I_ER OF TRAJECTORY F:_DINTS ? (50 TT_Aj.F__. MAXIMIJM)

4

WiLL BETA VALUES BE IN_T ?

NO

TYPE iN THE F LLOWiNG TI:_A.:EC'TORYVARIA_3LES SE_>E_AT D BY COMV_AS

50 TIMES _XiMUM

TIME(CEC) AI TF T q:(_T) VELOCi ...... _YtFT/SEC),AN_E 0_ _''-'r AC_ (DEG)

I

I .0,0.0,38! 5.0,20.0

2

2.0,0.0,382! .0,29.86

3

3.0,0.0,3821.0,39.98

4

4.0,0.0,3859.0,39.98

TllV_ ALTITUDE VELOCITY ANGLE ATTAC_

(SEC) (FT) (FT/SEC) (DEG)

I 0.1000E+OI O.O000E+O0 0.3816E+04 0.2000E+02

2 0.2000E+01 O.O000E*O0 0.3821E+04 0.2986E*02

3 0.3000E+01 O.O000E+O0 0.3821E+04 0.3998E+02

4 0.4000E+01 O.O000E+O0 0.3859E+04 0.3998E+02

I)0 YOU WISH TO C_-I/bNGEANY OF THE I'RAJECTORY INPUT ?

NO

DO YOU WISH TO WRITE "Tills INPUT TO A FILE ?

YES

WHAT IS II-IENEW FILE NAME ?

TRAJ.FIL

TRAJECTORY INPUT IS COMPLETE

ATMOSPHERE DATA

OPTIONS I. 1962 U.S. STAND/_RD ATMOSPHERE

2. WIND TUNNEL OPTION

3. INPUT ATMOSPHERIC DATA(ALT, T-INF,P-INF)

4. 1963 PATT_ICK AIR FORCE BASE ATMOSPHERE

5. 1971 VANDENBERG REFERENCE ATMOSPHERE

O_ION SELE_ED ?

2.0

WIND TUNNEL OPT ION

IS TI-IISOPTION CORRECTT ?

YES

B-16
WIND TUNNEL OPTION

INPUT STATIC TEMPERATURE AND PRESSURE AS A FUNCTION OF TIME.

TIME AND F_EESTIREAM VEL. ARE INPUT IN TRAJ. DAT_ WITH ALT. SET : 0.0

4 VALUES REQU

T-INF(R),P-INF(LB/SFT _

I

94.7,8.064

2

95.0,8.208

3

95.0,8.208

4

96.9,12.672

ARE ALL INPUTS CORRECT ?

YES

RED

DO YOU WANT TO RUN A HEATING INDICATOR ?

NO

HEAT TRANSFER METHOD

OPTIONS I. HEMISPHERE STAGNATION F_DINT

2, CATO/JOI-INSON SWEPT CYLINDER

3. ECXERT REF. ENT_ALPY FLAT PLATE METHOD

4. ECY,ERT/SPAULDING-C}-II %AT PLATE METHOD

5. BOEING RHO-'4U FLAT PLATE METHOD

6. BECKWITH/GALLAGHER SWEPT CYLINDER METHOD

7. BOEING RHO-MU SWEPT CYLINDER METHOD

8. LEES/DE'IRA-HIDALGO HEMISPHERE DISTRIBUTION

9. LEESIDE ORBITER HEATING

to. FLAP REATTACHMENT HEATING

11. FIN-PLATE PEAK NTERFERENCE HEATING

OPTION SELECTED ?

4.0

SHOULD RAREFIED FLOW HEATING BE INCLUDED ?

NO

IS THE HEAT TRANSFER OPTION CORRECT ?

YES

B-17
4. EC_::ERT/SPAULDING-CHI FLAT PLATE METHOD

RUNNING LENGTH (FT) ?

.209?

SURFACE DISTANCE TO START 0I_ TURBJLENT B.L.

THIS DISTANCE IS SUB_A$-ED F_O" T-E RUN_,!N3 LENGT_

FOR TURBULENT HEATING CALO. LA_I_S.

DES t_" _.... _-_

0.0

iS #_N AUTOV_IC _IRTUAL O_iS!N C_R_EC"!O_; DES!_E.: ?

NO

.6667

LAMINAR MANSLER FACTOR ?

!.0

REYNOLDS-A_,A£ OGY FACTOR

0. COLB URN

I. VON KAR MAN

DESIRED FACTOR ?

I.

ANY (}__NGES _

NO

* * * W#d_L OONDITIONS • * *

WALL TEMPERATL;_E (DES F) ?

0.0

WA_.L EMISSI#;TY ?

0.8

, , • CON'_INUATION O_--ION , , ,

IX) YOU WANT TO PROVIDE AN INITIAl. HEATING LOAD GT 0.0 (BTU/SQ.F-T) ?

NO

B-18
DO YOU WANT TO USE A HEAT "PRANSFER MULTIPLICATICN METHOD ?

NO

TRANSITION OPTIONS

OPT IONS I •

2.

3.

4.

5.

6.

7.

8.

TIME DEPENDENT: LAM TO TURB

TIME DEPENDENT: TURB TO LAM

REYNOLDS NO. DEPENDENT

RE-THETA

MDAC-E TR/b_ISITION

Iv{)AC-ETN3LE LOOK-UP

NAR RE VS ME TABLE LOOK-UP

RE-THETA/ME

Ol::q'lONSELECTED ?

1.0

I. TIME DEPENDENT: LAM TO TURB

TRANSITION BEGINS AT TIME(SEC) ?

3.2

FULLY TURDULENT AT TIME(SEC) ?

3.6

ANY CHANGES ?

NO

DO YOU WANT CROSS FLOW ADJUSTMENT OPTION ?

NO

B-19
FLOWFIELDANDLOCALPRESSUREOF:q_IONS

FLOWFIELD PRESSURE

-I. FLOWFIELDTYPENOTNEEDED -I. PRESSURETYPENOTNEEDED

I. SH#_RPWEDGESHOC}<ANGLE I. INPUTCPVS M_C_INO.TA_LE

2. SH#_RP_NE SHOCKANGLE 2. TANGENTWEDGEPRESSURE

3. OIBLIQUEANDNORMALSHO_ (90 DEG)3, TANGENTCONEPRESSURE

4. PARALLELSHOCK(PRESNOTNEEDED)4. Ot_LIQUESURFACEI:_RESSUrE

5. MODIFIEDNEWTONIAN

6. PRANDTL-MEYEREXP. (FF NOTNEEDED)

* * * * INPUTOPTIONS IN PAIRS WITH ASSOCIATED DELTA #_NGLES * * * *

(NOTE: TO SIGNIF-Y END OF CASE USE -1.0 FOR BOTH FF AND PRESS. OPTIONS.)

FLOWFIELD, DEL ANGLE,PRESSURE,DEL ANGLE

I

2.0,2.8,2.0,2.8

2

-!.0,O.Op-1.0pO.O

TOTAL EFFECTIVE ANGLE

SETI

FF SHRP-CX)NE ALPI_A + 2.800

P TAN-WE[X_E #_,PHA + 2.800

ANY OHANGES ?

NO

B-20
,i

DO YOU WANT TO USE TIME DEPENDENT GEOMETRY ?

YES

TIME DEPENDENT GEOMETRY

NUMBER OF TIME DEPENDENT ENTRIES ? (MA_=IO)

4

TIME(SEC),RADII(FT),LENGTH(FT),SLOPE OR SWEEP(DEG)

1.0,0.0,.2097,0.0

2.0,0.0,.1239,0.n

3.0,0,0,.0858,0.0

4.0,0.0,.0858,0.0

ANY CHANGES ?

NO

CONTROL FLAGS

YOU ARE COMPLETING INPUT FOR CASE I

WHAF IS TIIE BODY POINT NUMBER FOR CASE I ?

IO0

SHOULD LANMIN CREATE AN OUTPUT FILE FOR CASE

YES

Oo

I.

2.

PRINT CONTROL OPTIONS

DETAILED PR INTOUT

DETAILED PLUS SLIMM,_RYPRINTOUT

SUMMARY PR II_TOUT

NCTE: IF AN OUTPUT FILE IS TO BE CREATED EITHER

OPTION I. OR 2. MUST BE SELECTED

OPTION SELECTED ?

1.0

I ?

OUTPUT UN ITS OPT IONS

O. ENGL ISH

I. METR IC

OPTION SELECTED ?

O.

I S CASE

AS CASE

NO

2 ALONG THE SAME STREAMLINE

I ?

B-21
I •

2.

3.

4.

5.

ORIGINAL PAGE IS

OF POOR QUALITY

IINPUT CONTROL FLAG

•

NEW CASE FOLLOWS USING TITLE,TIMING AND T_AJ,

DATA FROM PREVIOUS CASE

END OF INF_jT (LAST CASE)

NEW CASE FOLLOWS USING T_Aj.DATA FROM FT4EVIOUS CASE.

NEW TITLE AND TIMING. INITIAL CASE DATA __I{I}_A,=_D. ] k_" ,

NEW CASE FOLLOWS USING NEW TiTLE,TIMi'_rc,,'F_AJ.ANr_ CASE DATA.

(INITIALLY ZERO w ARPAY)

SAME AS (l) EXCEPT ZERO ALL CASE DAT# rqO" PqEVIOJS CASE

SAME AS (3; EXCE=T INITIALIZF ZERO RLL T!_'_*_SA'_D CASE DATA

OF:q"ION SEP_ECWED ?

1.0

***** INPUT COMPLETE FOR CASE 1 *****

DO YOU WANT TO MAKE N_Y MODIFICATIONS TO CASE

NO

1 ?

CREATE OUTPUT FILE

WHAT IS ]'HE NAME OF TIIE OuTPuT FILE TO BE CI_EATED ?

PREM IN.OUT

WHAT IS 13-1ETITLE FOR CASE I ? (NOTE 72 C_AF:. LIMIT)

BOTTOM CENTERLINE HEATING TO GENERIC ORBITER AT MACH 8-TUNNEL B

INTERACTIVE INPUT FOR CASE 2

I S CASE

YES,

2 ATMOSPHERE DATA SANE AS FOR CASE I ?

mF

IS CASE

YES

2 WIND TUNNEL DATA S_ A_ FOR C#SE I

DO YOU WANT TO RUN A HEATING INDICATOR ?

NO

B-22
IS CASE

NO

2 HEAT_ANSFERDATASAMEASFORCAlF I

HEATTRANSFERMETHOD

OF_TIONS I. HEMISF_-_ERE 5T_',#,TIONPOINT

2. CATO/JOI-_NSON S_EP'TCYLINDER

3. ECXERTREF. EN,'D-J_PYFLATPLATEMETHOD

. EC_ERT/Sr_AUL_ING-CHI FLATPI.ATEMETHOD

5. BOEINGR_-<>-MGFLATPLATEMETHOD

6. BEC_KWiTH/GALLA6_IER SWEPTCYLINDERMED_OD

7. BOEING RHO-MU SWEPT CYL INDER METHOD

6. LEES/DETRA-_IDALGO HEMISPHERE DISTRIBU%ION

9. LEESIDE ORBITER HEATING

10. FLAP REATTAC_MENT HEATING

11. FIN-PLATE PEAK INTERFERENCE HEATING

OPTION SELECTED ?

4.0

SHOULD RAREFIED FLOW HEATING BE INCLUDED ?

NO

IS I'HE HEAT TRANSFER OPTION CORRECT ?

YES

4. ECXERT/SPAULDING-C: FLAT PLATE METHOD

RUNNING '_EN_IH _'" (FT) ?

.3532

SURFACE DISTANCE TO START OF TURBULENT B.L.

THIS DISTANCE IS SUBTRACTED FROM THE RUNNING LENGTH

FOR TURBULENT HEATING CALCULATIONS.

DESIRED LENGTH ?

0.0

IS AN AUTOMATIC VIRTUAL ORIGIN CORRECTION DESIRED ?

NO

TURBULENT MANGLER FACTOR ?

.6667

LAMINAR PANGLER FACTOR ?

1.0

REYNOLDS-ANALOGY FACTOR

0. OOLBURN

I. VON KA.RMAN

DESIRED FACTOR ?

I.

ANY CHANGES ?

NO

B-23
* * * I_ALL CONDITIONS * * *

WAIl TFMmFr, ATURF (DEG F) ?

0.0

WALL E!,_ISSIVIT¥ ?

0.8

DO .... TO

IS CASE

YES

2 TRANSITION DATA THE SAME F6:" CASE I ?

DO YOU WANT CROSS FLC)_'ACJJSTUl-'_NT OPT!ON ?

NO

IS CASE

NO

2 FLOVvFIELD DATA THE S&_E AS FOR CASE I ?

FLCW_'PIELD A',_ LOJA,L P_ESSJmE oP'riohs

FLOWFIELD PRESSURE ......

-I. FLOWFIELD TYPE NOT NEEDED -I. PRESSURE TYPE NOT NEEDED

I. SHARP WEDGE SHOCK ANGLE I. INPUT CF' VS MAC_ NO. TABLE

2. SHARP CONE SHOCK ANGLE 2. TANGENT _EDGF PRESSURE

3. OBLIQUE AND NORUAL SHOCK (90 DEG) 3. TANGENT CONE PRESSURE

4. PARALLEL SHOCK (PRES NOT NEEDED) 4. OBLIQUE SURFACE PRESSURE

5. MODIFIED NEWTONIAN

6. PRA_DTL-MEYER EXP. (FF NOT NEEDED)

B-2a
* . • , IN_T OPTIONS IN PAIRS WITH ASSOCIATED DELTA ANGLES t , , ,

(NOTE: TO SIGNIFY END OF CASE USE -1.0 FOR BOTH FF AND PRESS Ot_IONS.)

FLOWFIELD,DEL ANGLE, PRESSURE, DEL ANGLE

1

2.0,0.3,2.0,0.3

2

-I .0,0.0,-I .0,0.0

7-

FOTAL EFFECTIVE ANGLE

SETI

FF SHRP-CONE ALPHA + 0.300

"_ TAN-VvEDGE ALPHA + 0.300

ANY CHANGES ?

NO

DO YOU WANT TO USE TIME DEPENDENT GEO._ETRY ?

YES

IS CASE

NO

2 TIME DEPENDENT GEOMETRY DATA THE SN4E AS FOR CASE

TIME DEPENDENT GEOMETRY

NUMBER OF TIME DEPENDENT ENTRIES ? (MA.X=IO)

4

TIME(SEC),RADI I(FT),LENGTH(FT),SLOPE OR SWEEP(DEG)

1.0,0.0,.5692,0.0

2o0,0.0,.3152,0.0

3°0,0.0, .2277,0.0

4.0,0.0, .2277,0.0

ANY CHANGES ?

NO

I ?

B-25

.A- .-- h ASJL-'_.--" - •:....
CONTROL FLAGS

YOU ARE COMPLETING INPUT FOR CASE 2

WHAT IS THE BODY POINT NUMBER FOR C.ASE 2 ?

200

SHOULD LANMIN CREATE AN OUTPUT FILE FOR CASE

YES

2 ?

Oo

1.

2.

PRINT CONTROL OPTIONS

DETAILED PRINTOUT

DETAILED PLUS SUMMARY PRINTOUT

SUMMARY PRINTOUT

NOTE: IF AN OUTPUT FILE IS TO BE CREATED EITHER

O_ION 1. OR 2. MUST BE SELECTED

OPTION SELE_ED ?

1.0

OUTPUT UNITS OPTIONS

O. ENGLISH

I• METRIC

OPTION SELEC-'TED ?

O•

IS CASE

AS CASE

NO

3 AL_G THE S_E STREA_INE

2?

INPUT CONTROL FLAG

•

2.

3.

4.

5•

5.

NEW CASE FOLLOWS I'SING TITLE, TIMING A_D TRAJo

DATA FROM PREYlOU_ CASE

END OF INPUT (LAST CASE)

NEW CASE FOLLC_VS USING TRAJ.DATA FROM PREVIOUS CASE•

NEW TITLE AND TIMING. INITIAL O.#_SEDATA UNCHANGED.

NEW CASE FOLLOWS USING NEW TITLE, T!MiNG, TRAJ. AND CASE DATa.

(INITIALLY ZERO W ARRAY)

SAIvE AS (I) EXCEPT ZERO ALL CASE DATA FROM PREVIOUS CASE

SAME AS (3) EXCEPT INITIALIZE ZERO ALL TIMING AND CASE DATA

OPTION SELECTED ?

1.0

***** INPUT COMPLETE FOR CASE 2 *****

DO YOU WANT TO MAKE ANY MODIFICATIONS TO CASE

YES

B-26

2 ?
MODIFICATION SECTIONS

I .

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

12.

TIMING PARAME_RS

TIRAJECTORY DATA

ATNK)SPHERE DATA

FLC)_tFIELDAND F:_RESSUREDATA

C_OSSFLC_W DATA

TRANSITION CRITERIA

HEAT TRANSFER OF_TION

HEATING HULTIPLIERS

GEO_TRY DATA

CONTIROL PARAMEXER_

HEATING INDICATOR

OR C_HANGE A SPECIFIC VAJRiABLE IN W fkRRAY

SECTION TO BE MODIFIED ?

9.

IS CASE

NO

2 TIME DEPENDENT GEOMETRY DATA I-HE SNIE AS FOR CASE I ?

TIME DEPENDENT GEOMETRY

NUMBER OF TIME DEPENDENT ENTRIES ? (MA_X=IO)

4

TIME(SEC)oRADII(FT),LENGTH(FT)oSLOPE OR SWEEP(DEG)

I .0,0.0, .3532,0.0

2.0,0.0,.1943,0.0

3.0,0.0, .1448,0.0

4o0,0.0,.1448,0.0

ANY CHANGES ?

NO

DO YOU WISH TO HODIFY ANY OTHER SECTIONS FOR CASE

NO

2?

*N*** INF_JT OOMPLETE FOR CASE 2 ****_

DE) YOU WANT TO MAKE NIY MODIFICATIONS TO CASE

NO

INTERACTIVE INF:_JTFOR CASE 3

2 ?

IS CASE

YES

3 ATMOSF_rlEREDATA SAME AS FOR CASE 2?

B-27
IS CASE

YES

3 WIND TUNNEL DATA SAHE_AS FOR CASE 2 ?

DO YOU WANT TO RUN A HEATING INDICATOR

NO

IS CASE

NO

3 HEAT TRANSFER DATA SA_ AS FOR CASE 2 ?

HEAT TRANSFER IMETHOD

OPTIONS I. HEMISF:_-fERESTAGNATION F:_)INT

2. CATO/JOHNSON SWEF:_TCYLINDER

3. ECI<ERT REF. ENTHALPY FLAT PLATE METHOD

4. EC_<ERT/SPAULDING-CIHI FLAT PLATE METHOD

5. BOEING RHO-MU FLAT PLATE METHOD

6. BEO<WITH/GALLAGHER SWEFrF CYLINDER METHOD

7. BOEING F_-IC-MUSWEFTT CTLINDER METeOD

8. LEES/DETRA-HIDALGO HEMISPHERE DISTRIBLrTION

9. LEESIDE ORBITER HEATING

10, FLAP REA1-TACHMENT HEATING

11. FIN-PLATE PEAK INTERFERENCE HEATING

OPTION ;ELECTED ?

4.0

SHOULD RAREFIED FLOW HEATING BE INCLUDED ?

NO

IS THE HEAT TRANSFER OPTION CORRECT ?

YES

4. ECKERT/SPAULDING-CHI FLAT PLATE METHOD

RUNNING LENGTH (FT) ?

.5254

SURFACE DISTANCE TO ST/kRT OF TURBULE]_T _I:3.L.

THIS DISTANCE IS SUBIlRACTED FROM THE RUNNING LENGTH

FOR TURBULENT HEATING CALCULATIONS.

DESIRED LENGTH ?

0,0

IS _ /_UTOMATIC VIRTUAL ORIGIN CORRECTION DESIRED ?

NO

TURBULENT MANGLER FACTOR ?

.6667

L##IINAR MANGLER FACTOR ?

1.0

B-28
REYNOLDS-ANAL OGYFACTOR

0. COLBblRN

I. VONK#QRM_AN

DESIREDFACTOR?

I.

ANYC_ANGES?

NO

* * * WALLCONDITIONS* * _

WALLTEMPERATURE(DEGF) ?

0.0

WALLEMISSIVITY?

0.8

* * * CONTINUATIONOPTION* * *

DOYOUWANTTO PROVIDEAN INITIAL HEATINGLOADGT0.0 (BTU/SQ.FT)?

NO

IX) YOUWANTTOUSEA HEATTRANSFERMULTIF__ICATIONMETi_3D?

NO

IS CASE

YES

3 "rRANSITIONDATATHES#,'VIEFORCASE 2 ?

DOYOUWANTCROSSFLOWADJUSTMENTOPTION?

NO

IS CASE

NO 3 FLOWFIELDDATATHESAMEASFORCASE 2 ?

B-29
FLOWFIELDANDLOCALPRESSUREOPTIONS

FLOWFIELD PRESSURE .....

-1. FLOWFIELD TYPE NOT NEEDED -1. PRESSURE TYPE NOT NEEDED

I. SHARP WEDGE SHOOK ANGLE I. INPUT CI:VS MAC_I NO. TABLE

2. SHARP CONE SHOC_ ANGLE 2. TANGENT WEr_X_EPRESSURE

3. OE_LIQUE AND NORMAL SHOCK (90 DEG) 3. TANGENT CONE PRESSURE

4. PARALLEL SHOCK (PRES NOT NEEDED) 4. OBL!QL!E SURFACE PRESSURE

5. MODIFIED NEWTONIAN

6. PRANDTL-MEYER EXP. (FF NOT _EEDED)

* * * * INPUT OPTIONS IN PAIRS WITH ASSOCIATED DELTA ANGLES * * _'*

(NOTE: TO SIGNIFY END OF CASE USE -I.0 FOR BOTH FF AND PRESS. OPTIC'4S.)

FLOWFIELD,DEL ANGLE, PRESSURE, DEL ANGLE

I

2.0,0.0,2.0,0.0

2

-I.0,0.0,-I .0,0.0

TOTAL EFFECTIVE ANGLE

SETI

FF SHRP-CX)NE ALPI-IA + 0.000

P TAN-WEDGE ALPHA + O.OOO

ANY CHANGES ?

NO

DO YOU WANT TO USE TIME DEPENDENT GEOMETRY ?

YES

IS CASE

NO

3 TIME DEPENDENT GEOMETRY DATA THE SAME AS FOR CASE

TIME DEPENDENT GEOMETRY

2 ?

NUMBER OF TIME DEPENDENT ENTRIES ? (MA_X=IO)

4

TIME(SEC),RADII(FT),LENGTH(F-T),SLOPE OR SWEEP(DEG)

1.0,0.0,.5692,0.0

2.0,0.0,.3152,0.0,

3.0,0.0,.2277,0.0

4.0,0.0,.227?,0.0

ANY CHANGES ?

NO

B-30
OONTROLFLAGS

YOU ARE COMPLETING INPUT FOR CASE 3

W;_AT IS THE BODY POINT NUMBER FOR CASE 3 ?

3OO

SHOULD LANMIN CI_EATE AN OUTPUT FILE FOR CASE

YES

3 ?

O•

I.

2.

F_RINT CONTROL OFTIONS

DETAILED PRINTOUT

DETAILED PLUS SUMMJ_RY PRINTOUT

SUMMARY PR INTOUT

NOTE: IF AN OUTPUT FILE IS TO BE CREATED EITHER

OPTION I• OR 2. MUST BE SELECTED

OPTION SELECTED ?

1.0

OUTPUT UNITS OPTIONS

O. ENGL ISH

I. METRIC

OPTION SELECTED ?

O.

IS CASE

AS CASE

NO

4 ALONG THE SAME STREAMLINE

3 ?

I •

2.

3.

4.

INPUT CONTROL FLAG

e

6.

NEW CASE FOLLOWS USING TITLE,TIMING AND TRAJ.

DATA FROM PREVIOUS CASE

END OF INPUT (LAST CASE)

NEW CASE FOLLOWS USING "FRAJ.DATA FROM PREVIOUS CASE,

NEW TITLE AND TIMING• INITIAL CASE DATA UNCHANGED.

NEW CASE FOLLOWS USING NEW TITLE,TINING, TRAJ. AND CASE DATA.

(INITIALLY ZERO W ARRAY)

S/V/E AS (I) EXCEPT ZERO ALL CASE DATA FROM PREVIOUS CASE

SAME AS (3) EXCEPT INITIALIZE ZERO ,ALL TIMING NIC CASE DATA

OPTION SELECTED ?

2.0

B-31
***** INPUTCOMPLETE FOR CASE 3 *****

DO YOU WANT TO M,_KE ANY MODIFICATIONS TO CASE

NO

3 ?

*******'* OUTPUT FILE CO_,IPLETE ***w****

>

B-32
J

PREMIN OUTPUT FILE

WIND TUNNEL CASE

BOTTOM CENTERLINE HEATING TO GENERIC ORBITER AT MAC_ B-TUNNEL B

10 I .0000

130.2097000

14 3.2000

160.6667000

20 3.6000

230.8000000

27 1.0000 31

261 I .0000 262

453 95.0000 454

504 12.6720 .560

564 4.0000

5810.2097000

5820.123 9000

583 O.0858000

5840.0858000

611 100.0000 642

I0 _.0000 11

130.3532000

14 3.2000 15

160.6667000

20 3.6000

230.8000000

27 I.0000 31

370.3000000

380.3000000

261 I .0000 262

I.000

0.000

0.000

4.000

I.000

2.000

3.000

4.000

11 4.0000

15 I .0000

36.0000 32

2.0000 319

96.90O0 501

4.0000 561

1.0000 643

4.0000

1.0000

36.0000 32

453

504 12.6720 560

564 4.0000

5810.3532000

5820.1943000

5830.1448000

5840.1448000

611 200.0000 642

2.0000 319

95.0000 454 96.9000 501

4.0000 561

I.0000 643

1.000 4.000

0.000 0.000

1.000

0.000 3B16.000

0.000 3821.000

0.000 3821.000

0.000 3859.000

15.0000 37 2.8000 38 2.8000

1.0000 451 94.7000 452 95.0000

8.0640 502 8.2080 503 8.2080

1.0000 562 2.0000 563 3.0000

1.0000 647 1.0000 641 1.0000

15.0000

1.0000 451 94.7000 452 95.0000

8.0640 502 8.2080 503 8.2080

1.0000 562 2.0000 563 3.0000

1.0000 647 2.0000 641 1.0000

20.000

29.860

39.980

39.980

0.000

0.000

0.000

0.000

B-33
b

10 1.0000 11 4.0000

130.5254000

14 5.2000 15 1.0000

160.6667000

20 3.6000

230.8000000

27 1.0000 31 36.0000 32

319 1.0000 451 94.7000 452

501 8.0640 502 8.2080 503

561 1.0000 562 2.0000 563

5810.5692000

5820.3152000

5830.2277000

5840.2277000

611 300.0000 642 1.0000 643

15.0000 261

95.0000 453

8.2080 504

3.0000 564

1.0000 647

1.0000 262

95.0000 454

12.6720 560

4.0000

3.0000 641

2.0000

96.9000

4.0000

2.0000

B-34
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_c
APPENDIX C

PItF_IN CODE LISTING
C

C

C

C

C

C

C

C

C

C

C

C

C

C

PREMI N CODE

LANGLEY MINIVER PREPRC,_ESSORCODE

REMTECH, INC. 1983

BY:

C. ENGEL

C. SCHMI TZ

PH. 205-536-8581

PROGRAM _ IN

COMMON/WARRAY/W (700)

COMMON/WWAR AY/WW (700 )

COMMON/WWWARY/WWW (7O0 )

COMMON/UNIT/I IN, IOUT

OOMMON/T ITLE/I ITL I

COMMON/PCOEFF/TMCP (50),TCPM (50), NCF'MT

COMMDN/M ISC/NC, JFKS, TFLAG, MFLAG, ANSI

COMMON/I NP/N I,ND, IN SERT, NCPMTS, TMCPS (50 ),TCPMS (50),JFLAG, IADD

C

CHARACTER*20 FNAM6

CHARACTER*72 T ITL1

INTEGER ANS, TFLAG, ANS1, FLAG

I IN - INTERACTIVE INPUT UNIT NUMBER

lOUT - INTERACTIVE OUTPUT UNIT NUMBER

I IN=I

IOUT: I

C

C MFLAG = 0

C MFLAG = 1

C FLAG = 1

C FLAG = 1

C JFLAG = 1

C INSERT = 1

C TFLAG = 1

C FNAM6 -

C JFKS

C NC

C ND

C NI

C TITL1

C NCPMT -

C NCPMTS -

C TMCP -

C TMCPS -

C TCPM -

C TCPNS -

C _'

C WW -

C

ENGLISH UNITS

METRIC UNITS

CREATE NEW OUTPUT FILE

MODIFY AN EXISTING OUTPUT FILE

DELETED LAST CASE

CURRENT CASE AN INSERTION CASE

TITLE EXISTS FOR CURRENT CASE

NAME OF INPUT FILE TO BE MODIF',ED

- PROGRAM INPUT CONTRCL PARAMETER FOR PREVIOUS CASE

- CASE NUMBER

- NUMBER OF CASES DELETED

- NUMBER OF CASES INSERTED

- TITLE FOR A SET OF CASES

NUMBER OF ENTRIES IN PRESSURE OOEFFICIENT T/_BLE

SAVED VALUE OF NCPHT

MAO'I NUMBERS

SAVED VALUES OF T_ ARRAY

CP ARRAY

SAVED V.=LUES OF TCPM ,aRRAY

WORKING ARRAY OF W VALUE TO BE MODIFIED

W ARRAY MODIFIED TO DESIRED UNITS FOR OUTPUT

(INPUT ARRAY FOR LANMIN)

INSERT=O

NC_-O

C-I
NI=O

ND=O

MFL AG =1

JFKS=O

W(641 )=O.C

WRITE(lOUT,30)

30 FORIV_T(IHI,'INTERACFIVE INFWjT TO LARC MINIVER - LANMIN')

C CREATE OR MODIFY OUTPUT FILE

35 WRITE (lOUT, 36)

36 FORIVJ_T(///,IOX,'OUTPUT FILE METHOD'//,

$ IX,'I. CREATE A NEW OUTPUT FILE',/,

$ IX,'2. MODIFY AN EXISTING OUTPUT FILE',//,

$ IX,'OPTION SELECTED ?')

READ (IIN,*, ERR=35, END=gC _9)FLAG

IF(FLAG.EQ.I)C-_3 TO 20

C NAME FILE FOR MODIFICATION

10 WRITE (lOUT,!2)

12 FORMAT(//,IX,'WHAT IS THE NAME OF THE INPUT FILE ?_)

READ( IIN, 13, ERR=I O, END=9999)FNAM6

13 FORMAT (A20)

OPEN (UN IT=9, F ILE=F NAMS, STATb S= 'OLD', ERR=SBB8)

IF (MFLAG.EQ. I )WRITE(lOUT, 25)

25 FORIVL_T(/,IX,'INPUT FILE IS IN ENGLISW JNITS.',/,IX,

$ 'ALL CHANGES MUST BE IN ENGLISH UNIIS.',/)

M_AG=O

33 IF(IADD.EQ.I)GO TO 37

IF(FLAG.EQ.2)CALL INPUT(1)

IF(INSERT.EQ.I)GO TO 37

IF(JFLAG.EQ.I)GO TO 3

34 IF(FLAG.EQ.2)CM3 TO 200

C CHOOSE UNITS TO BE USED

20 WRITE(lOUT,21)

21 FORMAT(IX,'D<) YOU WANT TO INPUT DATA IN ENGLISH OR ',

$ 'METRIC 1')

READ( IIN, 45, ERR=20, END=9999) ANS

MFL AO =0

IF CANS. EQ. IHM) MFLAG= I

37 CDNT INUE

NC=NC+I

W (647 )=NC

C INPUT DATA FOR CASE

3 WRITE( lOUT, 38) NC

38 FORMAT(/,1X,'INTERACTIVE INPUT FOR CASE ',13)

IF(JFKS.OT.O)GO TO (2,9900,1,1,2,1)JFKS

1 CALL TIMI NO

IF(JFKS.EQ.3.0R. JFKS.EQ.6)C-_) TO 2

CAL L TRAJ

2 CALL ATM5

IF(W( 10).EQ.1.)CALL WNDTUN

IF (W( IO) .EQ.2. )CALL ATMDTA

39 WRITE (IOUT,40)

40 FORMAT(IHI,'DO YOU WANT TO RUN A HEATING INDICATOR ?')

READ( IIN, 45, ERR=3 9, END=9999) ANSI

45 FORMAT (At)

IF(ANSI.EQ. IHN)GO TO 50

C-2
IIIII.25 Illl_ I!JI!_ lJ,.4111.,.6
CALL MEATI N

GO TO 9000

.SO CALL HTRMTD

.54 WRITE(10UT,55)

.55 FORMAT(1HI,tDO YOU WANT TO USE A HEAT TRANSFER i,

$ 'MULTIPLICATION METNO0 ?l)

REAJ:)( I I N, 45, ERR=54, END=9999) ANS

i F(ANS. EQ. 1HY)CALL HTMULT

CALL TRKNS

69 WRITE(lOUT,70)

70 FORI%AT(1HI,'DO YOU WANT CROSS FLOW ADJUSTMENT OPTION ?')

READ( I I N, 45, ERR=69, END=9999) ANS

I F (ANS.EQ. 1HY)CALL CROSS

CALL FLOW(l)

89 WRITE (lOUT,90)

90 FORI_U_T(IHI,WDO YOU WANT TO USE TIME DEPENDENT GEOMETRY ?t)

READ( I I N,45, ERR=89, END=9999)ANS

IF(ANS.EQ. IHY )CALL TDGEOM

9000 CONTINUE

CALL (X)NTRL

200 CONTINUE

WRITE(IOUT, 10O)NC

100 "ORMAT(//,'X,'. w**** INPUT COI_LETE FOR CASE ', 13,' *****')

210 WRITE (IOl.rF,220)NC

220 FORMAT(/,IX,'DO YOU WANT TO MAKE ANY MODIFICATIONS TO ',

$ 'CASE ',13,' ?')

RFAD( IIN,45, ERR=21 O,END= 9999) ANS

IF(ANS.EQ. IHY)CALL MODIFY

IF(ANS.EQ. IHYIGO TO 200

CALL UNITS

CALL OUTPUT

IF(W(641).EQ.2.)GO TO 9900

ZERO W ARRAY ACCORDING TO PROGRAM INPUT OONTROL PARAMETER

OF LAST CASE

CALL INPUT(2)

IF(INSERT. EQ.I)GO TO 33

IF(JFLAG.EQ. I)FLAG=I

IF(FL/IK;.EQ.2)GOTO 33

GO TO 37

9900 WRITE (IOLF_,110)

110 FORMAT(//, IX, _****** OUTPUT FILE COME_LETE l****_,_,)

CALL EXIT

8888 CONTINUE

WRITE (I OUT, 8889) FNAM6

8889 FORMAT[/,IX, 'CANNOT OI::_:NFILE ' ,A20,/)

GO TO 10

9999 CONTINUE

CALL EXIT

END

C

C

C-3

liill C" "" .,I.
SUBROUTI NE I NPUT ( IB )

C

C THIS ROUTINE HAS 2 FUNCT.ONS

C IB = I ROUTINE READS IN W ARRAY DATA FROM OLD RUN FILE

C IB = 2 ZEROS OUT W ARRAY ACCORDING TO PROGRAM INPUT CONTROL

C PARAMETER OF LAST CASE

C JFK - PROGRAM INPUT CONTROL PARAMETER

C JFCP - PRESSURE COEFFICIENT INPUT OPTION

COMMON/W ARRAY /W (700 )

COlI_VION/UNIT/IIN, IOUT

COMMON/PCO EFF/TMCP (50 ),TCPM( 50 ),NCPIvFT

COMMC)N/T ITLE/T ITL I

COMMON/M ISC/NC, JFKS, TFLAG, MFLAG, ANSI

COMMOh/I NP/N i,ND, IN SERT, NCPM'FS,TMCPS (50),TCI::_4S (50 ),J_LAG, IF_]D

CHARACTER*72 TITLI

INTEGER ANS, TFLAG, ANSI

DIMENSION L(5),X(5)

CHECK FOR IB = 2

IF(IB.EQ.2)GO TO 5

C CHECK IF LAST CASE WAS AN INSERTED CASE

2

3

4

5

C

IF(INSERT.EQ.1)GO TO 400

NCI=NC+I

WRITE(IOUT,3)NC1

FORMAT(IX, l DO YOU WISH TO INSERT A CASE BEFORE CASE '

$ 13,' ?')

READ(IIN,4,ERR=2,END=9999)ANSS

IF(ANSS.EO. IHY)GO TO 300

FORMAT(At)

CONTINUE

JFK=W(641)+.O001

IF(IB.EQ.I)JFK=JFKS

JFKS=W(641)+.O001

IF(JFK.EQ.I.AND. IB.EQ.I)GO TO 160

IF(JFK.EQ.3)GO TO 130

IF(JFK.EQ.4)GO TO 100

IF(JFK.EQ.5)GO TO 120

IF(JFK.EQ.6)C_:) TO 110

IF(IB.EQ.2)GO TO 130

100 CONTINUE

DO 1000 J=1,700

1000 W(J)=O.O

C

110 DO 1100 J=lw8

1100 W(J)=O.O

C

ZERO W ARRAY ......

ZERO TIMING PARAMETERS AND PRINT OONTROL

121) DO 1200 J=9,49

1200 W(J)=O.O

DO 1300 J=201,210

1300 W(J)=O.O

DO 1400 J=261,650

1400 W(J)=O.O

IF(JFK.EQ.5.AND. !B.EQ.1 )GO TO 160

ZERO CASE DATA ---

C-4
150

C I_--

135

C

140

C

150

155

C

160

C

170

IF(JFK.EQ.6)GO TO 130

IF(IB.EQ.2)C-O TO 130

JFK=O

CONTI NUE

I F(IB.EQ.2)W(641 )=FLOAT(JFK)

IF( lB. EQ.2)IRETURN

TFLAG=!

READ(9,135)T ITLI

FORMAT (A72)

T ITLE

TIMING PARAMETER AND PRINT CONTROL

READ(9,!40) (W(J), J=1,8)

FORMAT (3F20.6)

IF(JFK.EQ.3.0R.JFK.EQ.6)GO TO 160

NUMBER OF TIME DEPENDENT TABLE ENTRIES FOR TRAJ.

READ( ';,I55)W(50)

FORMAT (3F20.6,2F 10.6 )

N=W(50)+.O001

NT=50+N

TRAJ DATA ....

RE_J](9,155 )(W(K), W(K+50), W(K+] 00), W(K+160), W(K+600) ,K=51 ,NT)

W(641)=0.0

RE;E)(9,175) (L(J),X(J),J=I ,5)

DO 171 J=1,5

171 IF(L(J).GT.O)W(L(J))=X(J)

17.5 FORMAT(5(13,F10.6) )

IF{W(641 ))170,170,180

180 CONTINUE

IF(W(641).NE.2.0)GO TO 18.5

CASE DATA .....

C

181

182

APPENDING CASES -

CASES AFTER THE ',

WRITE(IOLFT, 182)

FORMAT(/plXp'DO YOU WANT TO ADD ADDITIONAL

$ ICURRENT END CASE ?')

READ(!IN,4,ERR=181,END=9999)ANS

IF(AN3. EQ.1HY)IADD=I

185 CONTINUE

W(64_)=W(647)-FLOAT(ND)+FLOAT{NI)

JFK=W(641}+.O001

NC=W(647)+,O001

JFbF_-W(649}+.O001

IF(JFCP.LE.O)GO TO 210

READ(9,190)_

190 FORMAT(13)

READ(g,2OO)(TMCP(J)_TCF_4(J),J=I,NCPIWT)

200 FORMATI2FlO.6)

210 CONTINUE

IF(W(641).EQ.2.)CLOSE(UNIT=9,STATUS='KEEP')

C .............................. DELETED CASES --_

220 WRITE(IOUT,230)NC

220 FORMAT(lX, tDO YOU WISH TO DELETE CASE ',13, _ ?t)

READ(IIN,4,ERR=220,END=9999)ANS

IF(ANS. EO.1HN)GO TO 290

IF(W(641).EQ.2.)JFLAG=l

IF(JFLAG.EQ.1)GO TO 290

C-5
240 WRITE(IOUT, 250)NC, NC+1,NC

250 FORMAT(IX,'CASE '• 13,' DELETED. CASE 'P 13,' REDEFINED 'P

$ 'AS CASE 'D 13)

ND=ND+I

IF(NC.NE.I)GO TO 5

IF(JFK.EQ.4)GO TO 5

260 WRITE(lOUT, 270)

270 FORIVb_T(IX,'SINCE YOU WISHED TO DELETE CASE I DO YOU ALSO '

$ 'WANT TO DELETE THE ',,/IX,'TITLE,TIMING,AND TRAJ. TI-_AT'

$ 'CORRESPONDS TO CASE I ?')

READ(IIN,4,ERR=260,END=9999)ANS

IF(ANS.EQ. IHY)GO TO 5

GO TO 160

290 CONTINUE

RETURN

C

3OO

C

400

430

9999

CONTIt!UE

ANSS:'N'

INSERT=I

W(641)=FLOAT(JFKS)

GO TO 290

CONTINUE

I_SERT=O

NI=NI+I

NC=-NC+I

W(647)=FLOAT(NC)

WRITE(IOUT,3)NC

READ(IIN,4,ERR=430,END=9999)ANSS

IF(ANSS. EQ.IHY)GO TO 300

GO TO 5

CONTINUE

CALL EXIT

END

INSERTED CASES .....

LAST CASE IhSERTED -

J

C-6
C

C

C

C

C

SUBROUTI NE ATMDTA

ROUTINE FOR INPUTING ATMOSPHERE DATA FOR

OPTION 2

(X)MlVON/WARRAY/ W(700)

COMMON/UNIT/I IN, lOUT

OOMMON/MI SC/NC, ,_FKS, TFLAG, HFL AG,ANS1

ATMOSPHERE

INTEGER ANS, TFLAG, ANS1

MAY USE DATA FROM PREVIOUS CASE IF JFKS =I OR 3

IF (JFKS.NE. 1.AND. JFKS.NE.3)GO TO 9

NCN1=NC-1

1 WRITE ( I OUT, 2 ; NC, NCM1

2 FORHAT(1Hlp wIS CASE i P 13 P t ATNLSoDATA SALVEAS I P

$ tFOR CASE t,13,t 71)

READ( I I Nw100, ERR= 1pEND=9999) ANS

I F (ANS. EQ. 1HY)RE.tURN

9 CONTI NUE

10 WRi TE( I OUT, 20 )

20 FORMAT(///, t INPUT ATMOSPHERIC DATA1,//,

$ 1X, IFREESTREAN STATIC TEMPERATURE AND PRESSURE AS A

$ 1FUNCTION OF ALTITUDEI,/,1X, IO( t _I),I .50 MAXIMUM !

$ tVALUESf 10(i _t))

30 WRITE(lOUT,40)

40 FORMAT(tX, tHOW MANY ALTITUDE VALUES

READ( I IN, *,ERR=3O, END=9999) W(400)

C NALT = NUMBER OF ALTITUDE ENTRIES

NALT=W(400)+.O01

IF(MFLAG.EO.O)WRITE(IOUT,50)

I F (MFLAG. EQ. 1 )WRITE( I OUT,51 )

50

51

60

70

1000

80

90

1O0

9999

WILL BE INPUT 71)

FORMAT(lX, f ALTITUDE (FT) ,T- INF (R), P-INF (LB/SFT) t )

FORNAT( lX, i ALTITUDE (M) ,T- I NF(K) pp.. I NF(NEWTON/SQ. M) w)

DO 1000 I=I,NALT

WRITE(lOUT,70) I

FORMAT( 1X, 12)

REAl)( I IN*** ERR=60, END=9999) W(400+ I ),W(450+1 ),W(500+I )

CX)NTI NUE

WRITE ( I OUT, 90)

FORMAT(/,lX,'ARE ALL INPUTS CORRECT ?t)

READ( I I N, 100, ERR=80, END=9999) ANS

FORMAT(A1)

IF(ANS, EQ,1HN)GO TO 10

RETURN

CONT INUE

CALL EXIT

END

I

C°7
I

?

C

C

C

C

C

SUBROUTINE ATPIS

9

10

20

30

40

50

60

ROUTINE THAT CHOOSES ATMOSPHERE OFrTION TO BE

(X]I_ON/WARRAY/W (7O0 )

COMMON/UNI T/I I N, I OUT

COMMON/_I SC/NC, JFKS, TFL AG, MFLAG, ANSI

USED

C_HARACTER*40 (I-fAR(5)

INTEGER ANS, TFLAG, ANSI

TITLES FOR ATMOSPHERE OPT!ONS

DATA Or_P/'1 962 3.S. STAN_I_RD ATPE)SF_IEREt,

$ 'WIND TUNNEL OPTION',

$ 'INPUT ATMOSPHERIC DATA(ALTpT-INF, P-INF)',

$ '1963 PATRICK AIR FORCE BASE ATMOSPHERE t,

$ '1971 VANDENBERG REFERENCE ATMOSPHERE'/

USE ATMS. DATA FROM PREVIOUS CASE IF JFKS = I

IF(JFKS.NE.I.AND. JFKS.NE.3)GO TO 9

NC_41=NC-1

1 WRITE ( I OUT, 2 ) NC, NCM1

2 FORMAT(1HI,,'IS CASE t,13,' ATMOSPHERE DATA

$ 'FOR CASE ',13, v ?l;

READ( IIN,60, ERR=I ,END=9999) ANS

IF (ANS. EQ. IHY )RETURN

CONT INUE

WRITE( lOUT,20) ( I,Qi/_R(I),I=I,5)

FORMAT(///,5X, 'ATMOSPHERE DATM ,//,IX, 'OPTIONS

$ 11,t. ',A40,/,4(11X, I1,t. ',A40,/),

$ /,IX,'OPTION SELECq'ED ?t)

READ( IIN,% ERR=I O,END=gg9g) W( IO)

J= IFIX(W(10) )

WRITE( IOUT, 3 O)OINR( J )

FORMAT(/, IX,A40)

WR ITE (IOUT, 50)

FORMAT(/,IX, t lS THIS OPTION CORRECT ?')

READ( IIN,60, ERR=40, END=gggg)ANS

FORMAT(At )

IF(&NS.EQ.IHN)GO TO 10

IF(W(IO) .LT.4.)W(IO)=W(IO)-I.

RETURN

9999 CONTINUE

CALL EXIT

END

OR3

SAME AS J

C-8
SUBROUTINE OONTRL

C

C ROUTINE FOR SETTING CONTROL FLAGS

COMMON/WARRAY/W (700)

COMI_DN/UNIT/I IN, IOUT

COMMON/M ISC/NC, JFKS, TFL AG, MFLAG, ANSI

COIv_4ON/STRM/ISTRM, NNC

C

C

INTEGER ANS, TFLAG,ANSI

ISTRM=O

NC= W (647 )

10 WRITE( lOUT,20)

20 FORMAT( IHI, 10X, '_NTROL FLAGS',//)

30 CONTINUE

50 WRITE( IOUT, 60) NC

60 FORMAT (IX, 'YOU ARE COMPLETING INPUT FOR CASE ',13)

65 FORMAT (At)

70 WRITE(IOUT,80)NC

80 FORMAT(/,IX,'WHAT IS THE BODY POINT NUMBER FOR CASE ',

$ 13,' ?')

READ (IIN, _,ERR=7 O,END =9999) W (611 )

90 WRI TE( I OUT, 1O0) NC

100 FORMAT(lX, tSHOULD LANMIN CREATE AN OUTPUT FILE FOR CASE '

$ ,t3,' ?')

READ (IIN,65, ERR= 90, END= 9999 )ANS

IF(ANS. EQ. IHY)GO TO 110

W(643)=0.0

CK) TO 120

110 W(643)=I.0

C CHECK FOR HEATING INDICATOR OPTION

120 IF(ANSI.EQ. IHY)GO TO 140 /* HEATING INDICATOR W(642)=2.0

C PRINT OPTION

WRITE ( I OUT, 130)

130 FORMAT(/,IOX,WPRINT OONTROL OPTIONS',/,

$ lX,'O. DETAILED PRINTOUT',/,

$lX, ll. DETAi' ED PLUS SUMMARYPRINTOUT',/,

$ lX,'2. SUMMARYPRINTOUT',//,

$ IX,'NOTE: IF AN OUTPUT FILE IS TO BE CREATED EITHER ',/,

$ lX,'OPTION 1. OR 2. MUST BE SELECTED',//,

$ IX,'OPTION SELECTED ?')

READ( I I N, t, ERR=120, END=9999) W( 642 )

C OUTPUT UNI TS OPTI ON ---

140 WRI TE ( I OUT, 1.50 )

150 FORMAT(//,IOX,'OUTPUT UNITS OPTIONS',//,

$ 1X, '0. ENGLISH',/,

$ 1X,'1. MEI'R IC' ,//,

$ lX, IOPTION SELECTED ?')

READ( I IN, *, ERR=I 40, END=9999) W(648)

C

160

170

SI3REAMLINE OPTION --

WRITE(IOUT, 170)NC+I,NC

FORMAT(//,IX,'IS CASE ',13,' ALONG THE ',

$ 'SAHE STREN4LINE',/,IX,'AS CASE ',13,' ?')

READ(IIN,65, ERR=160,END=9999)ANS

IF(ANS. EQ. IHY)C.W)TO 200

C-9
C ...................... PROGRAM INPUT CONTROL PARAHETERS ......

!80 WRITE(IOUT, IgO)

Igo FORMAT(//,IOX,'INPUT OONTROL FLAG',//,

$lX, tl. NEW CASE FOLLOWS USING TITLE, TIMING AND TRAJ. ',

$ /,6X, tDATA FROM PREVIOUS CASEI,/,

$ IX,'2. END OF INPUT (LAST CASE)',/,

$ IX,_3. NEW CASE FOLLOWS USING TRAJ.DATA FROM PREVIOUS ',

$ ICASE.',/,6X.'NE--W TITLE AND TIMING. INITIAL CASE DATA ',

$ 'UNCHANGED.',/,

$ IX,'4. NEW CASE FOLLOWS USING NEW TITLE,TIMING,TRAJ. ',

$ 'AND CASE DATA.',/,6X,'(IN!TIALLY ZERO W ARRAY)',/,

$ IX,'5. S._4_EAS (I) E×CEP'F ZERO ALL CASE DATA FROM ',

$ 'PIREVIOUS CASE',/,

$ IX,'6. SAHE AS (3) EXCEPT INITIALIZE ZERO ALL TIMING ',

$ 'AND CASE DATA',//,

$ IX,'OP"TION SELECTED ?')

READ(IIN,%ERR=180,END=9999)W(641)

TO 300

C S]3RE_dvILINE CASES

200 CONTINUE

W(641)=I.0

CALL SllREAM

300 CX)NTINUE

RETURN

9999 CX)NTINUE

CALL EXIT

END

C-IO
C

C

SUBROUT INE CROSS

ROUTINE TO O..IOOSECROSS FLOW OPTIONS

COMI4ON/WARRAY/W( 700 )

CXDIvIvIC)N/UNIT/IIN, IOUT

CX)_N/M ISC/NC, JFKS, TFL AG, MFLAC, ANSI

C

INTEGER ANS, TFLAG, ANSI

C MAY USE CROSS FLOW DATA FROM PREVIOUS CASE IF JFKS

IF(JFKS.NE.I.AND. JFKS.NE.3)GO TO 9

= I CWR3

NCMI=NC-I

I WRITE(IOUT,2)NC, NCMI

2 FORMAT(///,' IS CASE ',13,' CROSS FLOW DATA ll-IESAME AS ',

$ 'FOR CASE ',13,' ?')

READ(IIN, 160,ERR=1,END=9999)ANS

IF(ANS.EQ. IHY)RETURN

9 CONTINUE

10 WRITE(lOUT,20)

20 FORMAT(///,IX, IOX,'CROSS FLOW A_)JUSTMENTS',//,

$ I0X,'I. CONSTANT WIDTH RECTANGLE(IDEAL GAS)',/,

$ I0X,'2. CONSTANT WIDTH RECFTANGLE(REAL GAS)',/,

$ I0X,'3. SHARP EDGE DELTA WING(IDEAL GAS)',/,

$ I0X.'4. SHARP EDGE DELTA WING(REAL GAS)',//,

$ IX,'OPTION SELECTED ?')

READ(IIN,_,ERR=IO,END=9999)W(201)

IT=IFIX(W(201))

GO TO (I00,200,300,400)IT

GO TO 500

C ..... C_ROSS FLOW OPTION I

100 IF(MFLAG.EQ.O)WRITE(IOUT, 110)

IF(MFLAG.EQ.1)WRITE(IOUT, 111)

110 FORMAT(//,IX,'I. CONSTANT WIDTH RECTANGLE(IDEAL GAS)',

$ //,IX,'RECTANGLE WIDTH(FT) ?')

111 FORMAT(//,IX,'I. CONSTANT WIDTH RECTANGLE(IDEAL GAS)',

$ //,IX,'RECTANGLE WIDTH(M) ?')

READ(IIN,_,ERR=1OO,END=9999)W;202)

120 IF(MFLAG.EQ.O)WRITE(IOUT, 130)

IF(MFLAG.EQ.I)WRITE(IOUT, 131)

I)0 FORMAT(IX,'EDGE RADIUS(FT_ ?')

I)I FORMAT(IX,'EDGE RADIUS(M) ?')

READ(IIN,_,ERR=-120,END=9999)W(205)

140 WRITE(lOUT, 150)

150 FORMAT(IX,'ANY C_IANGES ?')

READ(IIN,160,ERR=140,END=9999)ANS

160 FORMAT(AI)

IF(ANS.EQ. IHY)GO TO 100

GO TO 600

C .................... CROSS FLOW OPTION 2

200 IF(MFLAG.EQ.O)WRITE(IOUT,210)

IF(MFLAG.EQ.1)WRITE(IOUT,211)

210 FORMAT(//,IX,'2. CONSTANT WIDTH RECTANGLE(REAL GAS)',"

$ //,IX, tRECTANGLE WIDTH(FT) ?t)

211 FORMAT(//,IX,'2. CONSTANT WIDTH RECTANOLE(REAL GAS)',

$ //,IX,'RECTANGLE WIDTI-I(M)?')

READ(IIN,_,ERR=200,END=9999)W(202)

C-11
|!

220 IF(MFLAG.EQ.O)WRITE(lOUT, 130)

I F (MFLAG.EO. 1)WRITE( lOUT, 131 )

READ( I I N, ", ERR=220, END=9999) W(205)

230 WRtTE (lOUT,240)

240 FORMAT( I×, 'REAL GAS VELOCITY GRACI%NT

$ 'SURFACE, I.O SWEPT CYLINDER) ?')

READ(I IN,%ERR=230pEND=9999)W(204)

250 WRITE( lOUT,150)

READ( IIN,160,ERR:230,END:9999)ANS

IF(ANS. EQ. IHY)GO TO 200

GO TO 600

(0.31 FLAT '

C CROSS FLOW OPTION 3

300 WRITE(lOUT,310)

310 FORI_AT(//,IX,'3. SHARP EDGE DELTA WING(IDEAL GAS)',

$ //,IX,'DELTA WING SWEEP ANGLE(DEG) ?_)

READ(IIN,%ERR=_CO, END=9999)W(203)

320 WRITE(lOUT, 150)

READ(IIN, 160,ERR=320,END=9999)ANS

IF(ANS.EQ. IHY)C_O TO 300

GO TO 600

C ............ CROSS FLOW OPTION 4

400 WRITE(lOUT,410)

410 FORMAT(//,IX,'4. SHARP EDGE DELTA WING(REAL GAS)',

$ //,IX,'DELTA WING SWEEP ANGLE(DEG) ?')

READ(IIN,%ERR:400,END:9999)W(203)

420 WRITE(lOUT,430)

430 FORIVLAT(IX,'REAL GAS VELOCITY GRADIENT(SHARP EDOE ',

$ 'DELTA WING = 0.31, POINTED CONE = 1.0) ?'7

READ(IIN,%ERR=420, END=9999)W(204)

440 WRITE(iOUT, 150)

READ(IIN, 160,ERR=440,END=9999)ANS

IF(ANS.EQ.tHY)GO TO 40G

GO TO 600

C

500 CONTINUE

WRITE(lOUT,510)

510 FORMAT(//,IX,'BAD OPTION',/)

GO TO I0

600 CONTINUE

610 WRITE(lOUT,620)

620 FORMAT(/,IX,'IS llIE OPTION CORRECT ?')

READ(IIN, 160,ERR=610,END=9999)ANS

IF(ANS.EQ. IHN)GO TO 10

RETURN

9999 CONTINUE

CALL EXIT

END

BAD OPTION

C-12
t

Ib

D_

C

C

C

C

C

C

C

C

C

C

C

C

SUBROUTINE FLOW(ID)

ROUTINE TO SET FLOWFIELD AND LOCAL PRESSURE

ID = I CREATING NEW FLOWFIELD DATA

ID = 2 MODIFYING OLD FLOWFIELD DATA

COMMON/WARRAY/W (? O0)

COMMON/UNIT/I IN, IOUT

COMMON/PCOEFF/TMCP ( 50 ) ,TCPM ( 90 ), NCPM'r

COMMON/MI SC/NC, JFKS, TFLAG, MFL,_¢S,ANS1

FF(N) - FLOWFIELD OPTION

FFA(N) - ANGLE CORRESPONDING TO FF(N)

P(N) - LOCAL PRESSURE OPTION

PA(N) - ANGLE CORRESPONDING TO P(N)

FNAIV_ - NAME FOR PRESSURE COEFFICIENT

DIMENSION FF (9) ,FFA(9),P(9),PA(9)

INTEGER ANS, TFLAG, ANS1

CHARACTER*IO CHARF(4) ,CHARP(6)

CHARACTER*20 FNAM5

5

C

1

2

9

DATA (}IARF/'SHRP-WEDGE ',

$ 'SHRP-CONE ',

$ 'OBLIQ/NORM',

$ 'PARALLEL '/

DATA CHARPI 'CP--VS-M.ACH t ,

$ 'TAN-WEDGE ',

$ 'TAN-CONE '

$ 'OBL I(_'SURF',

$ IMOO_NEWT" t

$ 'PRANDT-MEY '/

MAY USE FLOWFIELD DATA FROM PREVIOUS CASE

IF(JFKS.NE.I.AND.JFKS.NE.3)GO TO 9

NCMI=NC-1

WRI TE( I OUT, 2 ) NC, NCM1

FORMAT(IHI, |IS CASE ',13, t FLOWFIELD

$ 'FOR CASE ',13' ?')

READ( IIN,20,ERR=I •END=9999) ANS

IF (ANS. EQ. IHY )RETURN

CONT INUE

W(261)=I .0

W(262)=2.0

W(263)=0.0

W(264) =0.0

W(265)=0.0

W(266)=0.0

W( 26? ) =0.0

W(268)=0.0

W(269)=0.0

DO 5 I=I,9

FF(I )=-1.0

P( I )=-1.0

FFA(I )=0.0

PA( I )=0.0

CONTI NUE

C-13

OPT IONS

INPUT T._LE FILE

IF JFKS = I OR 3

DATA THE SAME AS ',
r .6

I

R I0 WRITE( lOUT, 15)

15 FOR_T(///, lOX, ' FLOWFIELD

20 FORNt_T(A1)

IF(ID.E_).I)GO TO 1000

C

AND LOCAL PRESSURE OPTIONS',//)

_L

Im

C CONVERT W ARRAY TO FLOWFIELD/PRESSURE TABLE

I00 CON FINUE

I=I

J=31

K--37

110 CONTINUE

IF(W(J).EQ.O.O.OR.I.GT.9)GO TO 500

IF(W(J).LT.30.)GO TO 200

IF(W(J).GT.37.)GO TO 120

FF( I)=W(J)-34.

FFA(I )=W(K)

GO TO 130

120 FF(I )--W(J)-35.

FFA( I)=W(K)

130 J=J+1

K=K+I

IF(J.EQ.37)J=46

IF(FF(1).EQ.4.)GO TO 300

200 IF(W(J).EQ.29.)GO TO 220

P(I )=W(J)-13.

PA(I )=W(K)

GO TO 23O

22_ P(I )=6.

PA(I )=W(K)

230 J=J+1

K=K+I

IF(J.EQ.37)J=46

300 I=I+I

GO TO 110

C

j

w_

C

5OO

EOrlO FLOWFIELD/PRESSURE DATA

CONTINUE

I=I

WR ITE (IOUT, 505)

505 FORMAT(///,IX,25X,'TOTAL EFFECTIVE ANGLE ')

510 WRITE (IOUT, 515) I

515 FORMAT(IX,' SET', 11)

IF(FF(I ).GT.O.O)WRITE(IOUT, 520)CHARF(FF(I )), (FFA(J),J=I, I)

320 FOR_AT(2X,'FF',6X,AIO, SX,'ALPHA + ',9(F7.3:,' + '))

IF(P( I).GT.O.O)WRITE( IOUTj.525)CHARP(P( I)),(PA(J),J=I , I)

525 FORMAT(2X Ipi "/X,AIO,5X, IALPHA + t 9(F-/.3.,t + I))

l=1+1

IF(FF(I )°EQ.-1.0.AND.P(I ).EQ.-1.0)GO TO 600

GO TO 510

600 WRITE(lOUT, 610)

610 FORMAT(//,IX,'ANY O-IANGES ?t)

READ (IIN,20, ERR=600, END= 9999) ANS

IFCANS.EQ.IHY)GZ) TO 1000

GO TO 2000

C-14
III,

II,

D

It,

- i

b

ILl

ii,

r

C INPUT FLOWFIELD/PRESSURE DATA

1 000 CONTINUE

1 O10 WRITE ( I OUT, 1 O1.5)

1015 FORNAT(///,1X,6( t __)pt FLOWFIELDt 6(t _t),3X,6(w __),

$ t PRESSUREtp6( t -t),/,1Xtt-1. FLOWFIELD T'YPE NOT NEEDED I,

$ 8X,t-1. PRESSURE TYPE NOT NEEDED t,/,2x,, t 1 . SHARP WEDGE t,

$ tSHOCK ANGLEt,llX, W1. INPUT CP VS HACH NO. T/_LEV,/,2X,

$ _2. SHARP OCNE SHOCK ANGLEt,12X, t2. TANGENT WEDGE PRESSURE t,

$ /,2X, t3. OBLIQUE AND NORMAL SHOCK (90 E)EG)',lX,

$ t3. TANGENT CONE PRESSUREt,/,2X, t4. PARALLEL SHOCK (PRES w

$ tNOT NEEDED)_,2X,_4. OBLIQUE SURFACE P1RESSURE',/,39X,

$ t5. MODIFIED NEWTONIANt,/,39X, t6. PRANDTL-MEYER EXP. t,

$ t(FF NOT NEEDED)t,//,lXa4( t *t) t INPUT OPTIONS IN PAIRS I,

$ tWITH ASSOCIATED DELTA ANGLESt,4( t *t),/_IX, t(NOTE; TO t

$ ISIGNIFY END OF CASE USE -1.0 FOR BOTH FF AND PRESS. t

$ IOPTIONS.) t,/,lX, tFLOWFIELD, DEL ANGLE,PRESSURE, DEL ANGLE r )

DO 1020 1"1,9

1 030 WRI TE ( I OUT, 103.5) !

1 035 FORMAT( lX, 11 )

READ( I INp % ERR=I 030, _'ND=9999)FF ( I ), FFA( I ),P( I ), F'A( I )

IF(FF(I).EQ.-1 ..AND.P(t ._.EO.-1 .)GO TO 500

1 020 CONTINUE

C CONVERT FLOWLIELD/PRESSURE T/E_LE TO iV ARRAY

2000 CON'I'I NUE

DO 2001 1=1,9

IF(FF( I),GT.2,0)FF(I)=FF(I )+.35,0

IF(FF( I ),GE. 1 ,O,AND.FF(! ).LE.2.0)FF(I )=FF(I )+.34.0

IF(P(I ),EQ,6.0)P(I )=29.0

2001 IF(P(I).GE, l.0.AND.P(I).LE.5.0)P(I)=P(I)+13.0

I=1

J=31

JPlsJ+I

K=37

KPlsK+I

2100 IF(FF(I).EQ.-1..AND.P(I).EQ.-1.)GO TO 3000

IF(P(I).EQ.-1 .)GO TO 2300

IF(FF(I ).EQ.-1 .)GO TO 2200

W(J)=FF(I )

W(K)=FFA(I )

W(JP1)=P(I )

W(KP1)=PA(I )

J=J+2

K=K÷2

21.50 I=1÷1

JPI==J+I

KPI,=K+I

IF(J.EQ,37)J=46

IF(J,EQ.38)J=47 "

i F (JPI .EQ.37) J=46

!F(JP1 .EQ.38) J=47

GO 1"0 2100

2200 W(J)=P(I )

W(K )=PA( I )

J=J+l C-15
2300

C

K,-K.+I

G.O TO 21.50

W(J)=FF ( I )

W(K)=FFA( I )

J=J+l

K=K+I

GO TO 21 50

C C}_ECK FOR PRESSURE TYPE I

3000 _NTINUE

DO 3001 L=1,9

30_I IF(P(L).EQ.14.03GO TO 3100

GO TO 5OOO

3_00 CONTINUE

WRITE( IOUT,31103

3110 FOR_T(IHI,IOX,'INPUT PRESSURE

$ 'T/W_LE')

COEFICIENT VS. MA(3-1NO. '#

C

C

3130

3135

C

W(6493=I .0

3120 WRITE(10UT,3125)

3125 FORMAT(IX,'IS THERE AN INPUT FILE AVAILABLE ?')

READ( IIN,20, ERR=-3120,END=9999) AN S

IF(ANS.EQ. IHN)GO TO 4000

INPUT MACH TABLE VIA FILE

WRITE (IOUT,313 5)NC

FORNIAT(IX,'WHAT IS THE FILE NAME FOR CASE ',13,' ?')

READ( IIN,3140, ERR=3130, END=99993 FNAIV5

3140 FORMAT (A20 )

OPEN( UN IT=8,F ILE=FNAIV5,STATUS= 'OLD', ERR=88883

READ(8,31603 NCPf_rT

3160 FORMAT(13)

WRITE ( IOLFT,3165) NCF>MT

3'05 ,-ORMAT(//,IX, 13,' MA[_I NUMBERS')

W_ ITE(IOb_T,3166)

3166 FOr'MAT(//,5X, 'M-INF' ,T21, 'CP' ,/)

I)0 3333 I=i ,NCPMT

REA_(8,3170)TMCP( I),TCPM( I)

3170 FORMA_(2FIO.6)

WRITE (iOUT, 3175)TMCP( I),TCPM (I)

3175 FORMAT( IX,2F I0.6)

3333 CONTINUE

G'I.OSE (UN IT=8, STATUS= 'KEEP' )

3180 WRII'E ( IOLFr,3185)

3185 FORNV_T(/,1X,' IS lldlS THE DATA YOU WAAIT ?')

REAl) ( I I N, 20, ERR=-31BO,END=9999) ANS

IF(ANS.EO.1HY)GO TO 5000

CLOSE (UN IT=B, STATUS= 'KEEP' )

TO 3120

C I NPUT MACI-I T,mBLEV I A TERMI NAI.

4000 WRITE(lOUT,4010)

4010 FORNIAT(1H1, 't _ t INPUT VIA TERMIN/_.

$ 'HOW MANY MACI-I NO.S WILL BE INPUT ?

READ( I IN, % ERR=4000, END=9999) NCl:_fr

WRITE(10U-,4015)

* *',II, IX,

(MAXIMUM OF 50)')

C-16
4015

4020

4025

4444

4030

4035

5000

8888

8889

999g

FORMP_T(IX,'M'-INF, CP')

DO 4444 I:I,NCPMT

WRITE(IOUT,4025)I

FORMAT(IX, 12)

READ(IIN,*,ERF_-4020,LND:g999)TMCP(1),T_(1)

CONTINUE

WRITE(lOUT,4035)

FORMAT(/,IX,'ARE THERE ANY CHANGES TO ll-IEINI%IT ?_)

READ(IIN,20,ERR=4030,£ND=9999)ANS

IF(ANS.EQ. IHY)C_) TO 4000

CONTINUE /* EXI; SUBROUTINE

RETURN

WRITE(lOUT,8889)

FORMAT(/,IX,'UN_LE TO OPEN FILE.')

GO TO 3120

CONTINUE

CALL EXIT

END

C-17
C

C

C

SUBROUTINE HEAT IN

C

C

10

20

30

40

ROUTINE FOR SET'rING W ARRAY VALUES

INDICATOR CASE

COMMON/WARRAY/W (700)

COMMON/UN IT/II N, I OUT

COMMON/TITL E/T ITL 1

FOR A HEATING

C}-_. A,RACTER*72 TITLI

INTEGER ANS

9999

WRITE(lOUT,20)

FORMAT(///,IX,'

FORMaT(At)

WRITE(lOUT,40)

FORMAT(IX,'

$ IX,'

$ 1X,'

$ IX,'

$ IX,'

W(12)=1.0

W(11)=I .0

W(24)=0.0

W(31)=38.0

W (37)=90.0

W(32)=18.0

W(38)=90.0

W (642 }=2.0

W(644)=0.0

W(646)=0.0

W(315)=I .0

RETURN

CX)NTINUE

CALL EXIT

END

HEATING INDICATOR',//)

FAY AND RIDDELL',/,

RADIUS = I FT SPHERE',/,

WALL l'El__ = 0 DEG. F',/,

LEWIS NO. = 1.0',/,

SUMMARY PRINT ONLY',/)

/* RADIUS

/* FAY RIDDELL

/* WALL TEMPERATURE IF)

/* OBLIQUE SHOCK

/* SHOCK AN_3LE

/_ MODI F I ED NEWTONIAN PRESSURE

/* BODY ANGLE

/_ SUMM/I_RYPRINT ONLY

/* LEWIS NO. = 1.0

C-18
C

C

C

C

30

C

IO0

110

C

200

210

SUBROUT INE H'rNJLT

ROUTINE TO SET HEAT TRANSFER MULTIPLICATION FACTORS

COMPK)N/WA.RRAY/W(7 O0)

C01_43N/UN I T/I I N, I OUT

COP.940N/MI SC/NC, JFKS, TFLAG,MFLAO, ANSI

INTEGER ANS, TFLAG, ANSI

MAY USE MULTIPLIER DATA FROM PREVIOUS CASE IF JFKS = I

IF(JFKS.NE.I.AND.JFKS.NE.3)GO TO 9

NOMI =NC-1

I WRITE(lOUT,2) NC, _1

2 FORNUL.T(///,IX, t lS CASE t P 13• t MULTIPLICATION FACTOR

$ 'THE "AME AS FOR CASE t•13•t ?t)

READ( I I N,30,ERR= 1• END=9999) ANS

I F (ANS. EQ. 1HY)RETURN

9 CONTI NUE

I 0 WRITE ( I our• 20)

20 FORMAT(///, lX, IOX, ' HEAT TRN_ISFER

$ //,,IXetOF'TION TYPESt,/,lOX,

$ I1. (X)NSTANT VALUEI,/,IOX•

$ 12. MULTIPLIER A FUNCTION OF TIME',/•IOX,

$ '3. MULTIPLIER A FUNCTION OF FREESTREAM MAOH NO.',

$ //,IX,_NOTE: MULTIPLIERS ARE MULTIPLIED(I.E. ',,

$ '/U4°t. IFICATION = TYPE1 *TYPE2*TYI:_r.3) ' ,//)

FORMAT( A1)

"_ ML:LTIPLIER TYPE 1

WRITE( IOur, 11 O)

FORMAT(If,IX, tl. ODNSTANT VALUE' ,/l,lX,

$ 'DO YOU WANT THIS TYPE ?t)

REAl)(IIN•30, ERR-100, END=9999) ANS

IF(ANS.EQ. IHN)GO TO 200

120 WRITE (lOUT, 130)

130 FORMAT( IX, _ENTER LAMINAR, TURBULENT VALUES')

READ( I I N, *, ERR=-120, END=99 99) W(18) • W(19)

140 WRITE ( IOur, 150)

150 FORMAT(IX:'ANY CHANOES ?t)

READ( I IN,30, ERR'I 40, END=Og99)ANS

IF(ANS.EQ.1HY)GO TO 100

MULT IPL IER TYPE 2

WRITE(IOur,210)

FORMAT(//,1Xot2. MULTIPLIER A FUNCTION OF TIME t,

$ //,lX, tDO YOU WANT THIS I'YPIZ ?t)

READ( I I N, 30, ERR=200, END=ggg9) ANS

IF(ANS.EQ.1HN)GO TO 300

220 WRI "rE( I OUT, 23 O)

230 FORMAT(1X,|NUt43ER OF TIMES (10 MAXIMUM) ?t)

READ( I I N, *, ERR=220 • END= 9999) W(321) )

240 WRI TE( I OUT, 250 )

250 FORMAT(IX, tTIME,L/U_ MULTIPLIER, TURB MULTIPLIER t)

IT=W( 320)+.0001

DO 1000 I=I,IT

260 WRITE(IOUT,265) I

265 FORMAT(12)

READ( I IN,*,ERR=260, END=9999)W(320+ I) •W(330"t'1 ),W(340+1 )

OR3

DATA

MULTI PL ICAT ION FACT(%RS'•

C-19
1000

270

C

3OO

3O5

310

315

320

330

C

CONT INUE

WRITE (IOUT, 150)

READ( IIN,30, ERR=270, END=9999)ANS

IF(ANS.EQ. IHY)GO TO 200

V4JLTIPLIER TYPE 3

WRITE (lOUT,305)

FORM,_T(//,IX,'3. MtJLTII:_.IERA FUNCTION OF FREESTRE/MwI',

$ ' MACH NO.',/,5X,'LINEAR INTERPOLATION IN LOG(M-INF)',

$ ' VS LOG(MUL_IPI_IER) SPACE',//,IX,'DO YOU W/_NT ]]-IIS',

$ ' TYPE ?')

READ( IIN,3 O,ERR=300, END=9999) ANS

IF(ANS.EQ. IHN)GO TO 400

WRITE( lOUT,315)

FORMAT(IX,33HNUMBER OF MAC_I 'S (10 T_tAXlMILJM)?)

READ (IIN,*,ERR=-31O,END= 999: )W (360)

WRITE (IOUT, 320)

FOR_T(IX,'M-INF,LAM MULT, TURB MULT')

ITT=W(360) +.0001

DO 2000 I=I,IXT

WRITE( IOUT, 265) I

READ( IIN,_,ERR=-330,END= 9999) W(360+ I),W(370+ I),W(380+ I)

TEST FOR VALUE LESS ]]-IP_N

IF(W(360+I ).LE.O.O)GO

IF(W(370+I ).LE.O.O)GO

IF(W(380+I ).LE.O.O)GO

GO TO 2000

333 WRITE(lOUT,335)

335 FORMAT( IX,'VALUE CANNOT BE LESS THAN OR EQUAL

WRI TE (IOUT, 320)

GO TO 330

2000 (X)NTINUE

340 WRITE(IOUT, 150)

READ( IIN,30, ERR=340, END=9999) ANS

IF(ANS.EQ. IHY)GO TO 300

C CHECK NUNBER OF TABLE ENIKIES (MIN=2)

IF(ITr.LT.2.0)GO TO 500

DO 3000 I=1, ITT.

C OONVERT TO L(X; VALUE

W(360+ I ) =ALOG10(W(360+1 ) )

W(370+ I )=ALOG1 0(W(370+1 ) )

W(380+ I)=ALOGI 0(W(380+I ))

3000 CONTINUE

400 CONTINUE

RETURN

500 WRITE(lOUT,510)

510 FORI_AT(IX,'MINIMUM NU_BER I_A(]-Il_K).= 2 t)

GO TO 310

9999 CONTINUE

C/M.L EXIT

END

OR EQUAL TO 0.0

TO 333

TO 333

TO 333

TO 0.0',/)

C-20
i

SUIBROUTINE HTRMTD

C

C ROUTINE FOF_ SELECTING HEAT TRANSFER METHO0

C

C XLEWNO - LEWIS NUMBER

CX)_.I:) N/WARRAY/W (700 )

COMMON/UNIT/I IN, IOUT

COMMON/M iSC/NC, JFKS, TFLAG, MFL AG, ANSI

C

(>IARAC-'TERm50C_'!AR(I_)

INTEGER /bNS,TFL_,/_NSI

C TITLFS FOR HEAT TRANSFER OPTIONS

D_TA C}-I/_R/'HEMISPHERE STAGNAT ION _ INT',

$ 'CATO/JOFINSON SWEPT CYLINDER',

$ 'ECXJ_RT REF. ENTHALPY FLAT PLATE IVETHOD',

$ 'ECKERT/SPAULDING-CHI FLAT PLATE METHO0,,

$ 'BOEING RHO-MIJ FLAT PLATE METHO0',

j,

'BECKWITH/G_J. LAGHER SWEPT CYLINDER ME'rl-lO0,,

$ 'BOEING RHO-MU SWEPT CYLINDER METHO0',

$ 'LEES/DETRA-H IDALGO HEMI SPHERE DIS'I'RIBLFTION',

$ 'LEESIDE ORBITER HEATING',

$ 'FLAP REAI-rACHIVENT HEATINO',

$ 'FIN-PLATE PEAK INTERFERENCE HEATINO'/

C MAY USE DATA FROM PREVIOUS CASE IF JFKS = I OR 3

IF(JFKS.NE.I.AND. JFKS.NE.3)GO TO 9

NCMI =NC-I

I WR ITE ( IOUT, 2 )NC, NCMI

2 FORMAT(IHI,' IS CASE 'P 13,' HEAT TR/_NSFER DATA SAME AS '#

$ 'FOR CASE ',13,' ?')

READ( iIN,70,ERR=I ,END=9999)ANS

IF (ANS.EQ. IHY )RETURN

9 CX)NTINUE

10 WRITE (lOUT, 20) (I,CHAR( I), I=1,11)

20 FORMAT(///,' HEAT TRANSFER MEII'IOO',//,IX,'OPTIONS',

$ 3X_12,'. ',A50,/,10(IIX, 12,'. ',A50,/))

C CHOOSE A HEAT TRANSFER METHO0

30 WRITE (lOUT,40)

40 FORMAT(IX,'OFrrlON SELECTED ?')

READ( IIN,*,ERR=3O, END=9999) W( 11)

50 WRITE( JOUT, 60)

60 FORMAT( IX,'SHOULD RAREFIED FLOW HEATING BE INCLUDED ?')

READ( IIN,70, ERR=-SO,END=9999) ANS

70 FORMAT (At)

W(646)=0.0

IF(ANS. EQ. IHY) W (646)=I .0

BO WRITE( lOUT, 90)

90 FORMAT(IX,' IS THE HEAT TRANSFER OPTION CORRECT ?')

READ( IIN,70,ERR=80, END=9999)ANS

IF(ANS.EQ. IHN)GO TO 10

C-O TO (100,200,300,400,500,600,700,800,900, IOOO, 1100) ,W( 11)

GO TO 1200

C HEAT TRANSFER METHOD I

100 IF (MFLAG. EQ.O) WRITE (lOUT,110)CHAR( I)

IF(MFLAO.EQ.I )WRITE( lOUT,Ill )CHAR(I )

110 FORMAT(IHI,'I. ',/k50,//,IX,'BODY RADIUS (FT) ?')

C-21
C

2OO

C

300

111 FORMAT(1H! , '1 . t , ASOp//,IX, tBODY RADIUS (M) ?t)

READ(I IN, _,ERR=lOO,END=9999) W(12)

120 WRITE( lOUT, 130)

130 FORMAT(IX,'LEWIS NO. = 1o0 OR 1.4 ?t)

READ( IIN,*,ERR=-120,END=9999)XLEWNO

IF(XLEWNO. EQ. I.0)W(315)=I .O

IF(XLEWNO.EQ. I.4)W(315)=0.0

IF(W(646).EQ. I.O)WRITE( IOUT, 140)

140 FORMAT(/,IX,'NCTE: RAREFIED FLOI_ OPTION HAS BEEN

160 WRITE( lOUT, 170)

170 FORM_T( IX,'ANY C}_ANGES ?')

READ( IIN, /O,ERR=I60, END=9999)A_4S

IF(ANS.EQ.IHY)GO TO 100

GO TO 130_

HEAT TRANSFER METHOD 2

IF(MFLAG.EQ. O)WRITE( IOUT, 210)CHAR(2)

IF (MFLAG.EQ. I )WRITE( lOUT,211 )CHAR(2)

210 FORMAT(IHI,'2. ',A.50,//,IX,'BODY RADIUS (FT) ?')

211 FORMAT(IHI,'2. ',A.50,//,IX,'BODY RADIUS (M) ?')

READ( IIN,*,ERR=200, END=9999) W(12)

220 WRITE(lOUT,230)

230 FORMAT(IX,'SWEEP ANGLE ?')

READ( IIN,*,ERR=220, END=9999)W(17)

240 WRITE(lOUT, 130)

READ (IIN, *,ERR=240, END =9999) XLEWNO

IF (XLEWNO.EO. ! .0)W(315)=I .0

IF(XLEWNO.EO. I .4)W(315)=0.0

260 WRITE(lOUT, 170)

READ( IIN,70, ERR=-260,END=9999) ANS

IF(ANS.EQ.IHY)GO TO 200

GO TO 1300

HEAT TRANSFER METHOD 3

IF(MFLAG.EQ.O)WRITE( lOUT,310)CH#,R(3)

IF(MFLAG.E_. I)WRITE(IOUT,311)CHAR(3)

310 FORM_T(IHI, '3. ',A.50,//,IX,'RUNNING LENOTH (FT) ?')

311 FORMAT(IHI,'3. ',A.50,//,IX,'RUNNING LENGTH (M} ?')

READ( IIN,*,ERR=300, END=9999)W(13)

320 WRITE(IOUT, 330)

330 FORMAT( IX,'TURBULENT MANGLER FACTOR ?')

READ( IIN,*,ERR=320, END=9999)W(16)

340 WRITE (lOUT, 350)

350 FORMAT(IX,'LAMINAR MANGLER FACTOR ?')

READ( IIN,% ERR=340, END=9999)W(15)

360 WRITE(lOUT, 370)

370 FORMATrlX, tSURFACE DISTANCE TO START OF TURBULENT B.L.',

$ /,IX,'THIS DISTANCE IS SUBTRACTED FROM TIIE RUNNING ',

$ 'LENGTH' ,/,IX, 'FOR TURBULENT HEATING CALCULATIONS. ',/,IX,

$ 'DESIRED LENGTH ?')

READ( IIN, % ERR=360, END=9999) W(354)

375 WRITE( IOLFT,376)

376 FORMAT(IX,'IS AN AUTOMATIC VIRTUAL ORIGIN CORRECTION ',

$ 'DESIRED ?')

READ( IIN,70,ERR=375, END=9999) ANS

IF(ANS.EQ.1HN)W(29)=O.O

IF (ANS. EQ.1HY)W(29) =I .0

C-22

SEL EC'TED.')
C

400

405

406

410

415

416

C

5OO

510

511

52O

525

526

380 WRITE( lOUT, 170)

READ( I IN,,70, ERR=380, END:9999)ANS

IF(ANS. EQ.1HY)GO TO 300

GO TO _3(30

HEAT TRANSFER METHO0 4

IF(MFL_.EQ.O)WR ITE( IOUT, 405)0-_R(4)

IF (MFLhG.EQ. I )WRITE( lOUT,406)CHAR(4)

FORMAT( IHI ,'4. ',A.50,//,IX,'RUNNING LENGTH (FT) ?')

FORMAT( IHI,'4. ',A50,//.IX,'RUNNING LENGTH (M) i")

READ( IIN,*, ERR=400, END-'9999)W(13)

WRITE (iOUT, 370)

READ( IIN,*,ERR--41O,END=9999) W(354)

WRITE (I0UT,416)

FOR_3(IX,' IS AN AUTOMATIC VIRTIJAL ORIGIN CORRECTION *,

$ 'DESIRED ?')

READ{ IIN,7O,ERR_415, END_9999)ANS

IF(ANS.EQ.1HN)W(29)=O.O

IF (ANS. EQ. IHY)W( 29)--I.0

420 WRITE(lOUT,330)

RE/_)(IIN, i,ERR=420, END= 9999)W (16)

430 WR ITE (IOUT, 350)

READ( IIN,*,ERRS430, END-9999)W(15)

440 WRITE(lOUT,445)

445 FORMAT(/pIX,,REYNOLDS-ANALOGY FACTOR' ,//, IIX,

$ '0. COLBURN',/,11X,'1. VON K/_RMAN',//pIX,

$ 'DESIRED FACTOR ?')

READ ( IIN,*,ERR=-440,END= 9999 )W (31 g)

IF(W(646).NE.1.O)C_.-_)TO 470

450 WRI'FE(IOUT,455)

455 FORMAT(/,IX, rRAREFIED FLOW OPTIONS',/,IIX,

$ 'O. CONE',/,11X,'1. FLAT PLATE',/,IX_

$ 'DESIRED OPTION ?')

READ( I IN,*,ERR=45 O,END=9999)W(314)

IF(W(314) .NE.O.O)GO TO 4"70

460 WRITE(lOUT, 465)

465 FORM,a,T(/,IX,'RAREFIED CONE OPTIONS' ,/,I IX,

$ '0. SHARP CONE',/,11X,'I. BLUNT CONE',/,IX,

$ 'DESIRED OPTION ?')

READ (I IN, *,ERR=460, END=9999) W(6.50)

470 WRITE(lOUT, 170)

READ( I I N, 70,,ERR=470, END=9999)ANS

IF(ARS. EQ.1HY)GO TO 400

GO TO 1300

HEAT TRN_SFER NETHCE) 5

IF (MFLAG.E0. O)WRITE (IOUT,51 O)C}IAR(5)

IF (MFL_. EQ. I)WRITE( IOUT,511 )C}IAR(5)

FORMb_T(IHI,tS. ',ASO,//pIX,'RUNNING LEI_GTII(FT) ?')

FORMAT(IHI,'5. ',A.SO,//,IX,'RUNNINO LERGTH (N) ?')

READ( IIN,_,ERR=500, END-ggg9) W(13)

WRITE (I OUT,37O)

READ( I I N, *, ERR=520, END=9999) W(_54)

WRITE ( ! OUT, .526)

FORlulAT(1X,'IS AN AUTOMATIC VIRTUAL ORIGIN

$ 'DESIRED ?'7

READ( I I N,7 O, ERR=.525, END=9999)ANS

C-23

CORRECT ION ',
C

700

C

8O0

EIO

811

820

825

825

830

83.5

IF(ANS. EQ.1HN)W(29)--O.O

IF (ANS. EQ. IHY)W(29):I .0

530 WRITE(IOU',170)

READ( I!N, 7O,ERR:53 O,END:9999) AN S

IF(ANS.EQ. IHY)GO TO 500

GO TO 1300

HEAT TRANSFER METHOD

IF (MFL AC_.EQ.O)WR ITE (IOUT, 610)CH_(6)

IF (MFL_,S.EQ. I)WHITE( lOUT,611 )C_-(NR(5)

610 FORMAT( IHI,'6. ',_O,//,!X,'R_IUS (FT) ?')

611 FOR_T(IHI,'6. ',&50,//,IX,'RADIUS (M) ?')

READ( !IN,*, ER_--603,END=9999)W(12)

WR ITE(IOUT,620)

620 FORMAT(/,IX,'NOTE: THIS OPTION IS USED WITH ]'HE PARALLEL ',

$ /,7X,'SHO0< FLO_ FIELD OPTION 4 • TIIE SWEEP' ,/,TX, 'ANGLE 'p

$ 'IS CALCULATED USING THE AJNGLE',/,7X,'OF ATTACK + INPUT ',

$ 'ANGLE WIT]'IFF OFFION 4.')

IF(W(646) .EQ.I .O)WRITE (lOUT,630)

630 FORMAT(/,IX,'NOTE: THE RAREFIED CYLINDER OFq'ION HAS

$ 'SELECTED ')

640 WRITE(IOUT, 170)

READ(I IN,7 O,ERR=640, END=9999) ANS

IF(ANS. EQ.IHY)GO TO 600

GO TO 1300

HEAT TRAAISFER METHO0 7

IF (_iFLAG. EQ.O )WR ITE(IOUT, 71 O)CHAR(7)

IF(MFL_G.EQ.I )WRITE( IOUT,711)CH_R(7)

710 FORMAT(1H1, '7 . ' , A50,//,IX,'RADIUS (FT) ?')

711 FORMAT(IHI,'7. t,PL50,//,IX,'RAPIUS (M) ?')

READ(I IN,%ERR=-700,END=9999)W(12)

720 WRITE(lOUT, 620)

730 WRITE( lOUT, 170)

READ (IIN,7 O,ERR=73 O,END= 9999) ANS

IF(ANS.EQ. IHY)GO TO 700

GO TO 1300

HEAT TIRANSFER METH90 8

IF(MFLAG.EQ.O)WRITE(IOUT,810)CHAR(8)

IF(MFLAG.EQ.I )WRITE(IOUT,B11)CHAR(8)

FORMAT(IHI,'8. ,,ASO,//,IX, IRADIUS (FT) ?')

FORMAT(IHI,'B. ',A.50,//,IX,'RADIUS (M) ?')

READ (IIN, % ERR=800, END = _999) W (12)

IF(MFLAG.EQ.O)WRITE(IOUT,825)

IF(MFLAG.EQ. I )WRITE( I0UT,826)

FORMAT(IX,'RUNNING LENGTH (FT) ?')

FORMAT(IX,'RUNNING LENGTH (M) ?')

READ( IIN,% ERR=820, END=9999) W(13)

WR ITE (IOUT, 83.5)

FORMAT(IX, oLOCAL BODY SLOPE (DEG.) ?')

REA_)(IIN,% ERI_-830,END=9999) W (17)

WRITE (IOUT, 840)

840 FORM_T(/,IX,'NOTE: THIS OPTION IS USED WITH',/,

$ 7X,'FF OFI'ION 3. OBLIQUE AND NORMAL SHOCK, SHOCK ',

$ 'ANGLE _ 90.' p. /,7X,' P OPTION 5 • MODIFIED '•

$ 'NEWTONIAN, ANGLE = BODY SLOPE ')

850 WRITE (lOUT, 170) C-24

BEEN ',
READ( I IN, 70, ERR=850, END=9999) ANS

!F(ANS.EQ.1HY)GO TO 800

GO TO 1300

C .............. HEAT TRANSFER METHOD 9

900 IF (MFLAG.EQ.O) WRITE (IOUT,91 O)CHAR(9)

IF (MFLAG. EQ. I )WPI TE( lOUT,911 )CI_AR(9)

910 FORMAT(IHI,'9. ',A.50,//,IX,'FULL SCALE VEHICLE ',

$ 'USE RADIUS = 1.0 FT.',/jI×,'RADIUS (FT) ?')

911 FORMAT(IHI,'9. ',A.50,//,I×,'FULL SCALE VEHIC_.E ',

$ 'USE RADIUS = .3048 M.',/,IX,'RADIUS (M) ?')

READ( IIN,.,ERR=900,END=9999)W(12)

920 'F(MFLAG.EQ.O)WRITE(IOUT,925)

IF(MFLAG.EQ. I )WRITE( IOUT,926)

925 FORMAT(IX,:WINDWARD WALL ENTHALPY',/,IX,

$ '(480 BTU/LEM = 2000 R ASSUMED IF ZERO IS INPUT) ?')

926 FORMAT(IX,'WINDWARD WALL ENTHALPY',/,IX,

$ '(1.12E6 JOdLES/KG = 1111 K ASSUMED IF ZERO IS INPUT)

READ( IIN,*,ERR=920, END=9999)W(21 )

WRITE(lOUT,930)

930 FORMAT(/,IX,'NOTE: THIS OPTION IS USED WITH',/,

$ 7X,'FF OPTION 3. OBLIQUE AND NORMAL SHOCK, SHOCK ',

$ 'A_LE -"90.',/,7X,' P OPTION 5. MODIFIED NEWTONIAN,'

$ ' ANGLE = 90.')

940 WRITE( IOUT, 170)

RE/IJ3(IIN,7 O,ERR=940, END=9999) ANS

IF(ANS.EQ.IHY)GO TO 900

30 TO 1300

C HEAT TRANSFE_ METHOD 10

I000 IF(MFLAG.EQ.O)WRITE(IOUT, 1005)CHAR(10)

IF(MFLAG.EQ. I)WRITE( IOUT, IO06)CHAR(10)

1005 FORMAT(IHI,'IO. ',A50,//,IX,'RUNNING LENGTH ',

$ 'TO HINGE LINE (FT; _')

1005 FORMAT(IHI,'IO. ',A50,//,I×,'RUNNING LENGTH ',

$ 'TO HINGE LINE (M) ?')

READ( IIN,% ERR=I 000, END=9999) W(13)

1010 WRITE(lOUT,370)

READ (IIN,_,ERR=-101 O,END=9999) W (354)

1015 WRITE(IOUT, 1016)

1016 FORMAT(I×,'IS AN .'_JTOMATICVIRTUAL ORIGIN CORFECTION '

$ IDESIRED ?')

READ( IIN,70, ERR=I 015, END=9999)ANS

IF (ANS.EQ. IHN) W(29) =0.0

IF(ANS.EQ.1HY)W(29)=1.0

1020 WRITE ( I OUT, 1025)

1025 FORMAT(IX, t TURBULENT MANGLER FACTOR ? t )

READ( I INp*, ERR=-1020, END=9999) W(16)

1030 WRITE( IOLrl', 1035)

1035 FORMAT(1X,tLAMINAR MANGLER FACTOR ?t)

RE/E)( I IN, % ERR=-1030, END=9999) W(15)

1040 IF(MFLAG.EQ.O)WRITE(IOUT,1045)

I F (MFLAG. EQ. 1 )WRITE( lOUT, 1 046)

104._ FORMAT(IX,,FLFJ :_ LENGTH (FT) ?t)

1046 FORMAT(IX,,FLFJ _ LENGTH (M) ?')

READ(I IN,*,ERR=-1040,END=9999)W(22)

10.50 WRI TE ( IOUT, 1055 )

?')

C-25
1055 FORMAT(IX,'REYNOLDS ANALCX_Y FACTOR',/,IOX,

$ '0. COLBURN',/,IOX,'I. VCN KARMAN'_/,

$ IX,'DES!RED FACTOR ?')

READ(IIN,*,ERR=IC50,END=9999)W(319)

WRITE( IOUT• 1060)

1060 FORI_#_T!IX,'NOTE: FLAP ANGLE IS INPt_T TI'IROUGH ',

$ 'LAST PRESS. OPTION ANGLE.')

1070 WRITE(lOUT, 170)

READ( I IN, 70° ERR=lOT0, END=9999) ANS

IF(ANS.EQ.IHY)GO TO 1000

GO TO 1300

HEAT TRANSFER MET'r40O 11

IF(MFLAG.EQ.O)WRITE (IOLFT, 1 I05)CHAR( 11 )

IF (MFLAG.EQ. I )W_ITE ()Od3,11 06 )CHA,R(11 )

1105 FORMAT( IHI, '11 . ',A59,//,1X,'RUNN!NG LENGTH '•

$ 'TO FIN LEADING EZ_SE (FT) ?')

1106 FOR V_T(1H1,'11 • ',#.50,//,IX,'RUNNING LENGTH '•

$ 'TO FiN LEADING EDGE (M) ?')

READ(I IN,*,ERR=I IO0,ENC=9999)W(13)

1110 WRITE(lOUT,370)

READ( IIN,*, ERR=-I 1I0, END=9999)W(354)

1115 WRITE( lOUT, 1116)

1116 FORMAT(IX,' IS #_N AUTOMATIC VIRTIJAL ORIGIN CORRECTION '

$ 'DESIRED ?')

READ( I IN,70,ERR=1115,END=9999)ANS

IF(ANS.EQ. IHN)W(29)=O.O

IF (ANS. EQ. 1HY)W(29) =I .0

1120 IF(MFLAG.EQ.O)WRITE(IOUT, 1125)

IF (MFL AG. EQ. I)WR ITE (IOUT, 11 26 )

1125 FORI_VkT(IX,'DISTANCE ALONG FIN TO POINT OF INTEREST ',

$ '(FT) ?')

1126 FORMAT(IX,'DISTANCE ALONG FIN TO POINT OF INTEREST Y,

$ '(M) ?')

READ( IIN, *, ERR=I 120, END=C;999) W(25)

1130 WRITE (lOUT, 1135)

1135 FORMAT(IX,'FIN ANGLE AT ALPHA - BETA = 0 (DE3) ?')

READ( IIN, *, ERR=I 130, END=9999) W( 26 )

1140 WRITE(IOUT, 1145)

1145 FORMAT(IX,'FIN ANGLE OPTION' ,/,I OX,

$ '0. FIN ANGLE = INFMJT FIN AN_SLE',/,IOX,

$ 'I. FIN #J_OLE = INPUT FIN ANGLE + AtPHA'./,IOX,

$ '2. FIN ANGLE = INPUT FIN ANGLE + BETA',//,IX,

C

1100

$ 'OPTION DESIRED ?')

READ(IIN,*,ERR=-1140,END=9999)W(30)

1150 WRITE(lOUT,330)

READ(IIN,*,ERR=1150,END=9999)W(16)

1160 WRITE(lOUT,350)

READ(IIN, I, ERR=-I160, END=9999)W(15)

1170 WRITE(lOUT,445)

READ(IIN. I, ERR=11?O,END=9999)W(319)

1180 WRII'E(IOUT, 170)

READ(IIN, 70, ERR=IISO,END=99_9)ANS

IF(ANS. EQ.!HY)GO TO 1100

GO TO 1300

C BAD OPT ION --

C-26
CONTINUE

WR ITE( IOUT, 1210)

FORMAT(//, IX, iB_

GO TO I0

1200

1210

C

1300 CX)NTINUE

1310 IF(MFLAG.EQ.O)WRITE(lOUT, 1320)

IF(MFLAO. EQ. I )WRITE( IOUT, 1321 )

1320 FORMAT(///,IX,,* * * WALL CONDITIONS

$ 'WALL TEMPERATURE (DEG F) ?')

1321 FORM#T(///,IX,,* * * WALL CONDITIONS

$ 'wALL TEMPERATURE (DEG K) ?')

READ(I N,*,ERR=1310, END=9999)W(24)

OPTION',//)

SET WALL TEMPERATURE

* * *',ll,lX,

* * *',i/,IX,

C SET WALL EMISSIVITY

1330 WRITE(lOUT, 1340)

1340 FORMAT(IX,'WALL EMISSIVITY ?')

READ(IIN,*,ERR=1330,END=9999)W(2.3)

C .......... CX)NTINUATION OPTION

1400 IF(MFLAO.EQ.O)WRITE(IOUT, 1410)

IF(MFLAO.EQ.I)WRITE(IOUT, 1411)

1410 FORMAT(///,IX,'* * * CONTINUATION OPTION * * *',//,IX,

$ 'DO YOU WANT TO PROVIDE #_N INITI#J. HEATINO LOAD GT '

$ '0.0 (BTUISQ.FF) ?')

1411 FORIVtAT(///,IX,'* * * CONTINUATION OPTION * * *',//,IX,

$ 'DO YOU WANT TO PROVIDE AN INITIAL HEATING LOAD GT '

$ '0.0 (JOULED/SQ.M) ?')

READ(IIN,70,ERR=1400,END=9999)ANS

W(209)_.0

IF(ANS.EQ. IHY)W(209)=I.0

IF(ANS.EQ. IHN)C-O TO 1500

1420 IF(MFL_.EQ.O)WRITE(IOUT, 1430)

IF(MFLAG.EQ. 1)WRITE(IOUT, 1431)

1430 FORMAT(I_,'INITI_ LOAD (BTU/SFT) ?')

1431FORMAT(IX,'INITII_L LO_C) (JOULED/SQ.M) ?')

READ(IIN,*,ERR=I420, END=9999)W(316)

C TEST RAREFIED FLOW FLK;

1500 CONTINUE

IF(W(646).NE.1.0)GO TO 1600

GO TO (1600,1510,1510,1600,1510,1600,1510,1600,1510,1510

$ ,1510),W(11)

1510 WR ITE (IOUT, 1520)

1520 FORMAT(/,IX,'THE RAREFIED FLOW OPTION CANNOT BE USED WITH

$ 'HEAT TRANSFER',/,IX,'OFrI'ION SELECTED.',//,IX,

$ , * RA_REFIED FLOW OPTION IS DISENN_LED *',//,IX,

$ 'DO YOU WISH TO CI'I#_NGEHEAT TRA_ISFER _IONS ?')

W(646}=0.0

READ( IIN,70, ERR=I 51O,END=9_)99)ANS

IF(ANS. EQ. IHY)C-<)TO 10

1600 CONT INUE

RETURN

9999 CONTINUE

CALL EXIT

END

C-27

P
C

C

C

C

C

17

18

SLIBROUTINE MODI FY

THIS ROUTINE ENABLES USER TO PICK A SECTION OR ROUTINE

TO BE Me)r,iF IED OR REDEF INED

COM_N/_A,RRAY/W (700 )

COMMON/LNIT/I IN, !OUT

C'_)_C'_/_ISC/NC, JFKS,TF_.A@,MFL A_3,ANSI

I&TEGEq ANS, TFLAr_,ANS7

WRITE( IOUT,

FO_V_(///,

$ IX, ' I.

$ IX,, 2.

$ !X,' 3.

$ IX,' 4.

$ IX,' 5.

$ IX,' 6.

$ IX,' 7.

$ IX,' 8.

$ IX,' 9.

$ IX,'I0.

$ IX,'11.

$ IX,'12.

18)

IDX,'_SIF!CATiON SECT :O'_S',//,

TI_'.NG PARAMETERS',/,

TR,AJE_TORY DATA' ,/,

ATMOSmWE_E DATA' ,/,

FLO_FIELD AND PRESSURE DATA',/p

C:ROSSFLOW DATA' ,/,

TRANSITION CRITERIA',/,

HEAT TRANSFER OPTION',/,

HEATING MULTIPLIERS',/,

GEOMETRY DATA' ,/,

CONTROL PARAMETERS' ,/,

HEATING INDICATOR',/,

OR CHANGE A SPECIFIC VARIABLE IN W ARRAY',//

$ IX,'SECTION TO BE MODIFIED ?')

READ( IIN,*,ERR=17,END =9999)SECT

GO TO (I,2,3,4,5,6,7,8,9,10,11,12)oSECT

GO TO 17

I CALL TIMING

GO TO 30

2 CALL TRAJ

GO TO 30

3 CALL ATMS

IF(_(IC,).EO.I.)CALL _NDTU.N

IF(_,{ 10) .EQ.2.)CALL ATMDTA

GO TO 30

4 CALL FLO_(2)

GO TO 30

5 CALL CROSS

GO TO 30

6 CALL TRANS

GO TO 30

7 CAL L HTRMTD

GO TO 3O

8 CAt.L HTMULT

GO TO 30

9 CALL TDGEOM

GO TO 30

I0 CALL OONTRL

GO TO 30

11 CALL HEATIN

GO TO 30

12 rgo TO 200

30 WRITE ( lOUT, 40) NC

40 FOR#AT(/,IX,'DO YOU WISH TO MODIFY ANY OTHER SECTIONS

C-28
5O

C

200

210

220

230

2 40

25O

260

9999

'FOR CASE ',13,' ?')

READ( IIN, 50, ERR=30, END=9999) ANS

FORMAT (At)

IF (ANS.EQ. IHY"J:JO TO 17

RET_dRN

MOLiF_ A SPECIFIC

CONTINUE

WR ITE (IOutT,220 )

FORMAT(/,I×. WMAT IS :-_E W NU_E = rob W

READ( I 'N, *,ERP=2_ " _"'"-_" .....

WRITE( lOUT, 240) J

FORMAT(IX,tWHAT IS ,,'?HEVALUE FOR ,_(',{3,') ?')

READ(I IN,*,ERR=230, END=9999)_(J)

WRITE( lOUT, 260_

20RMAT(I×,'IS TY_.ERE #¢_OTHER W VARIABLE YOU WISH TO

$ 'C_ANGE ?')

I_EAD( IIN, 50, ERR=250, END=9999) ANS

IF(ANS.EQ.IHY)Cd.J TO 200

GO TO 30

CONTINUE

CALL EXIT

END

¢_ -,-r, A),i¢:I:" ? !

!

j,

C-29
C

C

C

C

C

SUBROUT!NE STREAM

ORIGINAL PAGE IS

OF POOR QUALITY

ROUT INE FOR CREATING STREAML INE CASES

X - X(FT) OR X(M)

SA - S_OCK ANGLE (DEG)

C _A - BODY ANGLE (DEG)

C BP - BOD.Y POINT NUMBER

C CASE- CASE NUMBER

C XPRT - -'R%RAM INPUT CONTROL PAP,AJWlETERFOR CASE

C J1 - ,,_INDEX FOR CASE

C J2 - W INDEX FOR X

C J3 - W INDEX FOR SA

C J4 - W INDEX FOq BA

C J5 - W INDEX FOR BP

C J6 - W INDEX FOR XPRT

C JK - FLAG FOR SPECIAL CASES OF STREA_I_INE

C CPARALLEL SHOCK OR PRANDT-MEYER OF'T_ONS)

COMMON/_AR RAY/W (700 )

CO_-_ON/UNIT/I IN, I OUT

COI_MCN/STRM/I STRM, NNC

COMMON/M ISC/NC, JFKS, TFL AG,MFLAG, AN $I

C

C

C

C

INTEGER TFLAG, ANSI

C

CHECK FOR TIME DEPENDENT GEOMETRY OPTION

IF(W(560).GT.O.O)GO TO 200

CREATE A,TEMPORARY FILE FOR STORING STREJV41.1NECASE DATA

OPEN (UN IT=4,F lLE= 'STRE AM.TMP', STATU S= 'UNKNOWN' )

NNC= NC+I

ISTRM=!

al =647

J2=13

C ....... DETERMINE SHOCK ANGLE A,T PREVIOUS CASE

DO 25 l=48_46,-I

111=I-3

25 IF(W(1).GT.34.AND.W(1).LT.40)GO TO 27

DO 26 I=36,31,-I

111=1+6

26 IF(W(I ).GT.34.AND.W(I ).LT.40)GO TO 27

27 JD= III

J3F=I

DETERMINE BODY ANGLE AT PREVIOUS CASE

DO 30 I=48,46,-I

I I--I-3

30 IF(_(1).GT. 13.AND. W(1).LT.30)GO TO 50

DO 40 I=36,31,-I

II=I+6

40 IF(W(I ).GT. 13.AND.W(I ).LT.30)GO TO 50

50 J4= I I

J4F=I

JK=O

C ....... C_tECK FOR PARA__LEL SHOOK OR PRANDT-MEYER CASES .....

I F (_( J4F ) .EQ. 29) JK=I

IF(jDF.GT. J4F) JK=2 C-30
2

3

4

5

6

7

60

70

C

80

IO0

200

210

9999

I F ( JK. EQ. 1) J4=0

I F(JK.EQ.2) J3=0

J5=611

J6=641

XPRT= 1.0

WEITE( lOUT, 1 )

ORIGINAL PAGE IS

OF POOR QUALITY

IF(MFLAG.EQ.O.AND. JK. EQ.O)WR;TE(lOUT,2)

IF (MFLAG.EQ.O.AND. JK.EQ. I)WRITE(lOUT,3)

IF(MFLAG.EQ.O.AND. JK. EQ.2)WRt TE(;OUT,4)

IF (MFL_.EQ. I .AND. JK.EQ.O)WRITE(lOUT,5)

IF (MFLAG. EQ. 1.AN_. JK.EQ. I)WRITE( IOUT,6)

IF (MFLAG.EQ. I .AND. JK. EQ.2)WRI TE (OUT,'/)

FORM_T(IHI,IOX,'STREAMLINE CASES',//,11X,'LIMITATIONS',/,5X, 'I'

,2X,'ALL L_TIONS ON STRENvtlNE HAVE NO INTERVENING SH_S OR,',

' EXPANSION FANS',/,5X,'*',2X,'MULTIPLIERS SAME FOR ALL X ',

'LCW_ATIONS',/,SX,'*',2X,'FIXED RUNN.NG LENGII-ISWITH ALRHA',/,

5X,'_',2X,'NOTE: SHOC,K ANGLE = SHOCK A_LE OR SHCW_K GENERATCWR ',

tANGLE',//,IX,'(INPUT DATA FOR EACH CASE - - USE NEG X ',

'TO INDICATE END OF DATA)')

FORMAT(/,IX, 'X(FT),SH_ ANGLE, BODY ANGLE, B.F .NO. ')

FORMAT (/,IX, 'X (FT), SHOC:IKANGLE, B.P.NO. ')

FORM,_T(/,IX, 'X(FT),BODY ANOLE, B.P. NO. ')

FORMAT(/,IX,'X(M),SHOC:K ANGLE,BODY ANOLE,B.P.NO.')

FORMAT(/,IX,'X(M),SHOCK ANGLE, B.P. NO. ')

FORMAT(/, IX, 'X(M) ,BODY ANGLE, B. P.NO. t )

WRITE (IOUT,70) NNC

FORMAT( IX, 13)

CASE=FLOAT (NNC)

F (MFLN3. EQ.O .AND. JK. EQ.O)READ(

F (MFLAG. EQ. O. AND. JK.EQ. I )READ(

F (MFLN3.EQ.0.AND. JK.EQ.2)READ(

F (MFLAG. EQ. I .AND. JK.EQ.O)READ(

F (MFL AG. EQ. I.AND. JK. EQ. I )READ (

F(MFLAG.EQ. I.AND. JK.E0.2)READ(

F (MFL_.EQ. 1)X=XI3.28084

WRITE

WRITE (4,80) J1,CASE, J2,X, J3,SA, J4,BA, JS,BP

WRITE (4,80) J6,XPRT

FORMAT(IX,5(13,Fg.4,1X))

IF(X.LT.0.0)GO TO 100

NNC=NNC+I

GO TO 60

CONT INUE

REWIND (UNIT=4)

RETURN

CONT INUE

WRITE( IOUT, 210)

FORMAT(/,IX,'CANNOT RUN STREAMLINE CASES

$ 'TIME DEPENDENT GEOMETRY.')

RETURN

CONT INUE

C/eL EXIT

END

IN,*,ERR=60, END= 9999) X, SA,BA, BP

IN, *,ERR=60, END= 99 "'9)X,SA, BP

IN,_,ERR=60,END=9999) X,BA, BP

IN, *,ERR=60, END= 9999) X, SA,BA, BP

IN,*,ERR=60,END=9999) X,SA,BP

IN, *,ERR=60, END =9999) X,BA,

TO I'EMPORARY FILE

AND USE ',

C-31
SUBROUT INE I'DGEOM

C

C ROUTINE FOR SETTING TIME DEPENDENT GEOI_TRY DATA

COMMON/WARRAY/W (700)

C'OMMON/UN IT/II N, IOUT

COMMC,'N/MI SC/NC, :FKS, TFL AG, MFL APo,AN SI

C

INTEGE_i ANS, TFLAG, ANSI

C MAY USE GEOMETRY DATA FROM PREVIOUS CASE IF JFKS = I OR 3

IF(JFKS.NE.I.AND. JFKS.NE.3)GO TO 9

NC'MI=NC-I

I WR ITE (IOUT, 2 )NC, NCMI

2 FORMAT(///,IX,'IS CASE ',13,' TIME DEPENDENT GEOMETRY ',

$ 'DATA THE SAME AS FOR CASE ',13,' ?')

REILD( IIN, 30, ERR=-I ,END=9999)ANS

IF (AN S. EQ. IHY )RETURN

9 ODNTINUE

I0 WRITE ( IOUT, 20)

20 FORMAT(///,IOX,' TIME DEPENDENT GEOMETRY',//)

30 FORMAT (AI)

C Q-IOOSE NUMBER OF TIME DEPENDENT ENI'RIE.c --

40 WRITE ( lOUT, 50)

50 FORMAT( IX, 'NUMBER OF TIME DEPENDENT ENIIRIES ? (MAX=IO)')

READ( IIN, % ERR=40,END=9999) II

W(560) =FLOAT(I I)

60 IF (MFLAG. EQ.O) WRITE (lOUT,70)

IF(MFLAO.EQ.I )WRITE( lOUT, 71)

70 FORMAT(IX,'TIME(SEC),RADII(FT),LENGTH(FT),SLOPE OR SWEEP',

$ '(DEG) ')

71 FORMAT(IX,'TIME(SEC),RADII(M),LENGTH(M),SLOPE_ OR SWEEP',

$ '(DEG) ')

C INPUT VALUES FOR EAO-I TIME

DO 1000 I=1,11

READ( IIN, *, ERR=60, END= 9999) W( 56(>+ I),W( 570+I ),W( 580+ I),

$ W(590+I )

I000 CT)NT INUE

80 WRITE( IOUT, 90)

90 FORMAT(IX,'ANY CFIANGES ?')

READ (IIN, 30, EI_cR=-80, END= 9999) ANS

IF(ANSoEQ. IHY)GO TO 10

I00 CX)NTINUE

RETURN

9999 CONTINUE

CALL EXIT

END

C-32
T

*i

i

C

C

C

C

C

C

SUBROUTI NE T I _,I NG

ROUTINE THAT SETS TIMING PARAMETERS AND PRINT CONTROL VALUES

SUM = TOTAL NUMBER OF PRINT TIMES

COMMON/WA.RRAYIW( 7O0)

COMMON/UNIT/I I N, IOUT

INTEGER ANS

SUM_ =0.0

SUN2 =0.0

SUM3=O .0

I0 WR ITE (IOUT, 20 )

20 FORMAT(IHI,SX,'SPECIFY PRINTOUT INTERVALS',/)

_,0 WRITE (lOUT,40)

40 FORMAT(IX, tINITIAL TIME (SEC) t)

RE _:)(IIN,% ERR=30, END=g999) W( I )

50 WRITE (lOUT,60)

60 FORMAT(IX, tPRINTOtlT INTERVAL I (SEC)I,IOX, tDELTA TIME t)

READ( lIN,'_,ERR=90, END= 9999)W(2)

?0 WRITE(iOUT,80)

80 FORMAT(IX, tSECOND TIME (SEC) w)

READ (IIN,*,ERR=?O, END-9999) W (.3)

IF(W(2).GT.O.O)SUMI=((W(3)-W(I))/W(2))

90 WRITE ( I OUT, I 00)

100 FORMAT(IX, tPRINTOUT INTERVAL 2 (SEC)t,IOX, IDELTA TIME')

READ( I I N, _,, ERR=90, END=9999) W( 4 )

110 WRITE(IOUT, 120)

120 FORMAT(IX, tTHIRD TIME (SEC) t)

READ( I IN, t, ERR=11 O, END=9999)W(5)

IF(W(4) .GT.O.O)SUM2=((WCS)-W(3))/W(4))

1.30 WRITE( lOUT,140)

140 FORMAT(IX°tPRINTOUT INTERVAL 3 (SEC)',IOX, tDELTA TIME')

READ (IIN, *,ERR=t3 O,END=g999) W(o)

150 WRITE( lOUT, IGO)

160 FORMAT(IX,'FOURTH TIME (SEC) t)

READ( IIN,**ERR= 150, END=9999) W (7)

IF (W(6) .GT.0.0 )SUM3=( (W("/)-W(.5))/W(6) )

W(8)=I .0

170 WRITE( lOUT,,180)

180 FORMAT(/, IX, t.A.RETHE PRINTOUT TIMES CORRECT ?t)

READ( I IN, 190,ERR=170, END=9999) ANS

190 FORNIAT(AI )

IF(ANS.EQ. IHN)GO TO 10

SUM=SUMI+SUM2+SUM3

C TEST FOR GREATER THAN I00 PRINT TIMES

IF(SUM.LT.IOO.)GO TO 1000

WRITE( IOUT_ 200)

200 FORMAT(/,IXwtMAXIMUM NUMBER OF TIMES(tO0) EXCEEDED. t,/)

GO TO 30

I 000 CONTI NUE

RETURN

9999 (X)NT INUE

GALL EXIT

END C-33
C

C

C

C

C

C

C

C

C

SUBROUTINE TRAJ

ROUTINE THAT COPIES TRAJ DATA TO W ARRAY

LINE - TRAJ TABLE LINE NUMBER

FNAMI - NAME OF IRAJ FILE

TITLE - TITLE OF TRAJ FILE

BFLA/_ : 0 YAW ANGLE NOT INCLUDED

BFLAG = I YAW ANGLE INCLUDED

COMMON/WARRAY/W (700)

COMMON/UNIT/I IN, IOUT

COMMON/M ISC/NC, JFKS,TFLAG, MFLAG, ANSI

CHAJ_,AC-"TER*20 FNAMI

CHARACTER*80 TITLE

INTEGER ANS, BFLAG, TFLAG, ANSI

C

10 WRITE(lOUT, 20)

20 FORMAT(IHI,IOX,'TRAJECTORY INPUT',/)

30 WRITE(lOUT, 40)

40 FORMAT(IX,'DO YOU HAVE A TIRAJECrORY

READ(IIN,50,ERR=30,END=9999)ANS

50 FORMAT(At)

IF(ANS.EQ. IHN)GO TO 130

INPUT FILE ?')

ORIGINAL PAQE I_

OF FOOR QUALITY

C INPUT TRAJECTORY VIA FILE

60 WRITE (lOUT,70)

70 FORMAT(IX,'WHAT IS TIIE FILE NAME ?')

READ( IIN,80,ERR=60, END=9999)FNAM1

80 FORMAT (A20)

OPEN(UN IT=7,F IL E=FNAMI ,STATUS= 'OLD', ERR=8888)

READ(7,85)T ITLE

85 FORMAT(A80)

C BFLAG = 1 IF YAW ANGLE INCLUDED

C W(50) - NUMgEP OF TIME DEPENDENT TABLE ENTRIES

READ (7,90) BFLAG, W(50)

90 FORMAT( 12,FI0.5)

NPTS--IFIX(W(50))

C READ TI_,ALT, VEL, ANGLE OF ATTACK,AND YAW ANGLE(OFTIONAL)

IF (BFLAG. EQ.O )READ (7,99, END=98) (W(50+ I),W(100+ I),W( 150+ I),

$ W(210+I ),I--I,NPTS)

IF (BFLAG.EQ. I )READ (7,I00, END=98) (W(50+ I),w( 10,0+I),W( 150+I ),

$ W(21(>_I),W(650+I ), I=I,NP'rs)

98 CONTINUE

99 FORHAT(4E 15.4 )

100 FORMAT(SE15.4)

IF(HFLAG.EQ.O)GO TO 103

DO 101 IZ=101,200

101 IV(IZ)=IV(IZ)/3.28084

103 CONTINUE

CLOSE(UN IT=7, STATUS= 'KEEP' )

C DISPLAY TRAJECTORY

104 CONTINUE

I--0

C-34

JiJrit_
105 CONTINUE

I F (BFL.=W;.EQ.O .AND. MFLAG. EQ.O) WRIl'E ( lOUT, 11 O)

I F (BFL/M;. EQ.O. AND. MFLAG. EQ. 1)WRI "rE( lOUT, 11 2)

I F (BFLAG. EQ. I .AND.MFLAG. EQ.O)WRI TE (lOUT, 111 )

I F (BFLAG. EQ. 1 .AND. MFLAG. EQ. 1 )WRITE ( lOUT, 113)

110 FORIVIAT(/,lX, t TIME ALTITUDE VELOCITY ANGLE ',

$ IAI'TACKt,/t (SEC) (FT) (FT/SEC) I,

$ t (DEG) ',/)

112 FORMAT(/,IX, t TIME ALTITUDE VELOCITY ANGLE t,

$ VATTACK',/,' (SEC) (M) (M/SEC) ',

$ ' (DEG) ',/)

111 FORMAT(/,IX,' TIME ALTITUDE VELOCITY ANGLE ',

$ 'AI-FACR BETA',/, I (SEC) (FT) (FT/SEC) t,

$ ' (DEG) {DEG) ',/)

113 FORMAT(/,lX,' TIME ALTITUDE VELOCITY

$ tAI"TACK BETA' ,/,' (SEC) (M)

$ t (DEG) (DEG) ,,/)

115 I=1+1

IF(BFLAG.EO.O)WRITE(IOUT, 120) I,W(50+I ),W(100+1 ),

$ W(190+I),W(210+I)

I F(BFLAG.EO.1 )WRITE (lOUT, 120) I, W(50+l ),W(100+1 ),

$ W(190+I),W(Z10+I),W(690+I)

120 FORP4AT(1X, 12,5E12.4)

IF(I.EO. NPTS)GO TO 210

IF(I .EQ.20.OR. I.EQ.40)READ( I IN, I 29,ERR=123,END=9999)

123 IF(I.EO.20.OR. I.EQ.40)GO TO 105

125 FORP4AT( lX )

GO TO 115

C

C

130

140

150

INPUT TRAJECTORY VIA TERMINAL

CX)NTI NUE

WRI TE( I OUT, 150 )

FORMAT(1X,'WHAT IS THE NUMBER OF TRAJEC'rORY POINTS ? ',

$ '(90 TRAJ.PTS. MAXIMUM) t )

RE/E)( I IN, t ERR=I 40, END=9999)NFTS

W (90) =FLOAT (NPTS)

160 WRITE( lOUT, 170)

170 FORMAT(IX,'WILL BETA VALUES BE INPUT ?')

REAl)( I I N, 90,ERR= 160, END=9999) ANS

BFLAG=O

I F ( ANS. EQ. 1HY)BFL/WE;=1

I F (BFL AG. EO• O. AND. MFLAG. EO. 0 ) WR! TE( I OUT, 180 )

I F (BFL AG. EQ. 0. AND. MFLAG. EQ. 1 ) WRI TE( I OUT, 182 )

! F ( BFLAG. EO. 1. AND. MFL/MS.EQ. 0 ) WRI "rE( I OUT, 181 )

I F (BFL/MS.EO. 1. AND. MFLAG. EO° 1 ) WRI TE( I OUT, 183 )

180 FORI_T(1X,"I'YPE IN THE FOLLOWII_W;TRAJECTORY VARI&BLES ',

$ 'SEPERATED BY CON_v, AS',/p11(' -'),' 50 TIMES M/O(IMIJMt,

$ 11(' .,),/ o TIME(SEC),ALTITUDE(FT),VELOClTY(FT/SEC),',

$ 'ANGLE OF ATTACK(DEG)')

182 FORHAT(IX, ITYPE IN THE FOLLOWING TRAJECTORY VARIAI3LES ',

$ tSEPERATED BY COMMAS',/,11( t _,) t 50 TIMES MAXIMLIMt,

$ 11(' _l),/ , TIME(SEC),ALTITUDE(M),VELOCI'rY(N/SEC)pt

$ tANGLE OF Al-rACK(DEG)t)

181 FORMAT(1X,'I'YPE IN THE FOLLOWING TRAJECTORY VARI/E}LES ',

$ tSEPERATED BY COMMAS',/p11(' _,) t 50 TIES NA)(IMUM_p

C-35

.t L
m l $ t1(' ,),/ t TIME(SEC),ALTITUDE(FT),VELOClTY(FT/SEC),

$ tANGLE OF ATT,_(DEG),BETA(DEG) t)

183 FORMAT(IX, ITYPE IN THE FOLLOWING TRAJECTORY V/URIABLES t

$ tSEPERATED BY COMMAS',/,11( t --t),t 50 TIMES MAXIMUMt,

$ 11 ( t -t),/ t TIME(SEC),ALTITUDE(M),VELC)CITY(M/SEC),t,

$ tANGLE OF ATTACK(DEG),BETA(DEG)I)

DO 1000 I=I,NPTS

190 WRITE (lOUT,200) I

200 FORMAT(IX, 12)

I F (BFLAG. EQ. O)READ ( I IN, i, ERR=I 90, END=9999) W(.50+I ),

$ W(IOO+I),W(150+I),W(210+I)

I F(BFL/I_C-.EQ.I )READ( I I N_.% ERI:_I 90,END=9999)W(.50+ I ),

$ W(IOO+I),W(150+I),W(210+I),W(650+I)

I000 CONTINUE

GO TO ! 04

C

C CHANGE TRAJ EC'TORY

210 WRITE(lOUT,220)

220 FORMAT(/,1X, tL-_ YOU WISH TO O-IANGE ANY OF THE tp

$ tTRAJECTORY INPUT ?t)

READ( I I N,50,ERR=21 O, END=9999)ANS

IF(ANS.EQ. 1HN)GO TO 280

260 CONTINUE

WRITE( I OUT,261 )

261 FORMAT(/,1X, tDO YOU WISH TO O-IANGE AN EXISTING LINE ?w)

READ( I I N, 50, ERR=-260, END=9999) ANS

IF(ANS.EQ. 1HY)C-_) TO 400

262 WRITE(lOUT,263)

263 FORMAT(IX,'IX) YOU WISH TO ADD A NEW LINE TO THE TRAJ.

READ( i IN, 50,ERR=262, END=9999)ANS

IF(ANS.EQ. 1HY)GO TO .500

264 WRITE(IOUTj265)

265 FORMAT(IX,'DO YOU WISH TO REMOVE A LINE FROM THE TRAJ.

READ( I I N,.50,ERR=264, END=9999)ANS

IF(ANS.E(_.IHY)GO TO 700

266 WRITE ( I OUT, 267)

257 FORMAT(lX_ 'DO YOU W_T TO O-IANGE THE WHOLE TRAJ. ?t)

READ( I IN, 50,ERR=-266, END=9999)ANS

IF(ANS.EQ. 1HY)C-K) TO 1.30

?')

-_t)

C

280

290

300

310

320

325

326

OOPY I'RAJECTORY TO F IL E

CONT INUE

WRITE (IOUT,300)

FORMAT(IX,'DO YOU WISH TO WRITE THIS INPUT TO A FILE ?')

READ (IIN,5O, ERR=-290,END= 9999) ANS

IF(ANS.EQ. IHN)GO TO 330

WRITE (IOUT,320)

FORMAT(IX,'WHAT IS THE NEW FILE NAME ?t)

READ( IIN,BO,,ERR=31O,END=9999) FNAMI

OPEN(UNI T=7,F IL E=FNAMI ,STATUS = 'NEW t)

WRITE (I0UT,326 )

FORMAT(IX,'WHAT IS THE TITLE OF THE TRAJECTORY ?t)

READ( I IN,8.5,ERR=-325,END=9999)T ITLE

WRITE(7,85)TITLE

WRITE (7,90 )BFL AG, W(.50)

C-3G

.-...-_... - _...-_,_-..-_-

i
IF (BFLtW.. EQ.O) WRITE (7,99) (W'(50+I)wW( 100+i ),W( 150+1 ),

$ W(21 0+1 ), I=1 ,NF"TS)

IF(BFLAG.EO.1 )WRITE(TpIO0) (W(50+l),,W(lO0+l ),W(150+1 )p

$ W(210+1 ),W(650+ I ), I=I,NPTS)

CLOSE( UNI T'7, STATUS= ' KEEPt )

:)30 WRI'TE(IOUT,:)40)

340 FORIMAT(/,IX, tTRAJECTORY INPUT

RETURN

IS COMPLETEt)

C CTIANGE A L I NE OF TRAJECTORY

400 CONTINUE

WRITE( I 0UT,410)

41b FORIVJ=,T(1X,tWHICi-I LINE DO YOU WISH

READ( I IN, *, ERR=400, END=9999)L INE

420

4.30

440

441

442

443

C

C

500

510

600

520

TO CI_ANGE ?')

IF(BFLAG.EQ.O)WRITE(IOUT, 120)LINE, W(50+LINE),W(100+LINE)p

$ W(150+LINE),W(210_LINE)

IF(BFLAG.EO.1)WRITE(IOUT, 120)LINE, W(50+LINE)pW(lOO+LINE),

$ W(150+LINE),W(210+LINE),W(650+LINE)

IF(BFLAG,EQ,O.AND.MFLAG.EO.O)WRITE(IOUT,440)LINE

IF(BFLAG.EQoO.AND.MFLAG.EQ,l)WRITE(IOUT,441)LINE

IF(BFLAG.EQ.1.^ND.MFLAG.EQ.O)WRITE(IOUTe442)LINE

IF(BFLAG,EQ.1.AND.MFL/E;.EQ.1)WRITE(IOUTp443)LINE

FDRMAT(/_IX, ITIRE(SEC),/_LTITUDE(FT)wVELOCITY(FT/SEC)p I ,

$ I/U_GLE OF ATTACK(DEG)

FORMAT(/tlX, tTIME(SEC)

$ _N'_IGLEOF ATTACK(DEG)

FORMAT(/_IX,'TIME(SEC)

',/plX, 12)

,ALTITUDE(M),VELOCITY(M/SEC), w,

',/plX, 12)

,,,M..TITUDE(FT),VELOCITY(F'r/SEC),t,

$ 'AI_oLE OF A'i-FACK(DEG),BETA(DEG)',/,1X, 12)

FORMAT(/,IX,'TIME(SEC),ALTITUDE(M),VELOCITY(M/SEC), ! ,

$ IAI_LE OF ATTACK(DEG),BETA(DEG)',/,1X,12)

IF(BFLAG.EQ.O)RE/E)(IIN,*_ERR=430,END=9999)W(50+LINE),

$ W(100+LINE)wN(150+LINE),W(210+LINE)

IF(BFLAG.EQ.1)READ(IIN,%ERR=430,END=9999)W(50+LINE),

$ W(100+LINE),W(150+LINE),W(210+LINE),W(650+LINE)

GO Tn 210

ADD A LINE TO TRAJECTORY

CONTINUE

WRITE(lOUT,510)

FORIVdkT(1XptWHAT IS THE NUMBER OF THE LINE YOU WISH lO ADD ?t)

REK)(IIN,*,ERR=500_END=9999)LINE

DO 600 K=NPTS, LINEt-1

J=K+I

W(50+J)=W(50+K)

W(IOO+J)=W(IOO+K)

W(1.50+J)=W(150+K)

W(IIO+J)-W(210+K)

W(650+J)=W(650+K)

{X)NTINUE

IF(BFL/E;.EQ.O.AND.MFL/W).EQ.O)WRITE(IOUT,440)LINE

IF(BFLAG.EO.O.AND.MFL/W).EO.1)WRITE(IOUT,441)LINE

IF(BFLAG.EQ,1.AND.MFL,'N3.EO.O)WRITE(IOU_,442)LINE

IF(BFLAG.EQ.1.AND.MFLAG.EO.1)WRITE(IOUT,443)LINE

IF(BFLAG.EO.O)READ(IIN,*,ERR=520_END=9999)W(50+LINE)p

$ W(lOO_LINE),W(150+LINE),W(210+LINE)

C-37

a .°

t" _ m
C

C

I F (BFL AL;. EQ. 1 )READ ( I I N, *, ERR=520, END=9999) W(50+L INE),

$ W(lOO+LINE),W(150+LINE),WC2I 3+LlI"E),W(650+LINE)

NPT S= NPTS+ I

W(50) -FLOAT (NPTS)

GO TO 210

DELETE A LINE OF TRAJECTORY

700 CONTINUE

WRITE( lOUT,7 I0)

710 FORMAT( IX, 'WHAT IS THE NUMBER OF

READ( IIN,*jERR=7OO,END = 9999)L INE

DO 800 J=LINE, NPTS-I

K=J+I

W( 50+J )=W( 50+K )

W(IOO+J)=W(IO0+K)

W( 150+J)=W(150+K)

W(210+J)=W(210+K)

W( 650+J )=W( 650+K )

800 CONTINUE

NPTS=NFTS-I

W(50) =FLOAT (NFrFS)

C-O TO 210

8888 CONT INUE

WR ITE (IOUT, 350) FNAMI

3.50 FORIV_AT(IX,'CANNOT OPEN ',A20)

GO TO 60

9999 CONTINUE

CALL EXIT

END

THE LINE YOU WISH TO DELETE ?')

OF POOR QUALiTy

C-38
SUBROUTINE TRANS

C

C RL,:TINE TO C_OOSE TRANSITION OPTION

COMMON/WARRAY/W( 700 )

CONIMON/UNIT/I IN, lOUT

CONI_ON/MISC/NC, JFKS, TFL AG ,MFL AG, AN$I

C

C

C

1O0

109

INTEGER ANS, TFLAG, ANS1

MAY USE TRANSITION DATA FROM PREVIOUS CASE IF JFKS : 1 OR 3

IF(JFKS.NE°I.AND.JFKS.NE.3)GO TO 9

NCM1=NC-1

I WRITE (1OUT, 23NC, NCMI

2 FORMAT(Iril,tlS CASE 1,13,1 TRANSITION DATA THE SAME t,

$ °FOR CASE t,13,t 71)

READ( IIN, '30, ERR=I, END=9999) ANS

IF (ANS. EQ. I_Y )RETURN

9 CONTINUE

10 WRITE(lOUT, 20)

20 FORMAT(///,IOX,' TRANSITION OPTIONS',//,IX,

$ 'OPTIONS 1. TIME DEPENDENT: LAM TO TURBV,/,

$ 11X,'2. TIME DEPENDENT: TURB TO LAM',/,

$ 11X,'3. REYNOLDS NO. DEPENDENT',/,

$ 11X,'4. RE-THETA',/,

$ 11X,_5. MOAC-E TRANSITION',/,

$ 11X,'6. MDAG-E TABLE LOCO-UP',/,

$ 11X,'7. NAR RE VS NIE T._BLE LOOK-UP',/,

$ 1IX,'8. RE- ,_I'IETA/ME',//,

$ IX,'OF'TION SELEC'TED ?')

REAl:)(IIN,t,ERR" IO,END=9999) W (27 )

IT= IFIX(W(273)

GO TO (100,200,300,400,500,600,700,800),IT

GO T3 900

TRANSITION OPTION 1 .....

WRITE ( I GUT, 105)

FORMAT(//,IX,'I. TIME DEPENDENT: LAM TO TURB',

$ //,IX, 'TRANSITION BEGI_IS AT TIME(SEC) 7')

READ( IIN, *,ERR=100, END=9999) W(14)

110 WRITE (lOUT, 115)

115 FORMAT(IX,'FULLY TURBULENT AT TIME(SEC) ?')

READ( IIN, t,ERR=-II0, END'9999) W(20)

IF(W(29).EQ.O.O)GO TO 118

116 WRITE(lOUT, lIT)

117 FORMAT( IX, 'A VIRTUAL ORIGIN CORRECTION CANNOT BE MADE ',

$'WITI'ITillS OPTION. I,/,IX,'RESET VIRTUAL ORIGIN OPTION ?')

READ( IIN,130, ERR'I 16, END= 9999) ANS

IF (ANS. EQ. IMY )W(29) =0.0

118 CONTINUE

120 WRITE(IOUT,125)

_25 FORNIAT(IX,'ANY O-IANGES ?')

REAl:)(IIi',130, ERR- 120, END- 9999) ANS

130 FORMAT(A1 )

IF(ANS. EQ.1HY)GO TO 10

GO TO 1000

TRANSITION OFrrlON 2 ......

WRITE (IOUT, 205)

C

200

"":'--"' _' PA3E I_

OF POOR QUALITY

C-39
C

30G

3O5

205 FORMAT(I/,IX,'F_. TIMEDEPENDENT:UR8TOLAM',II,IX,

$ 'FULLYTURBULENTATTIME(SEC)?')

READ(I IN,% ERR=-200,END=9999) W(14)

210 WRITE (IOUT,215)

215 FORMAT(IX,'LAMINAR, FLOW BEGINS AT TIME(SEC) ?')

REAr_(IIN,% ERR=-210,END=9999) W(20)

IF(W(29).EQ.O.O)GO TO 218

216 WRITE (IOUT,217)

2 _ FORMAT( IX,'A VIRT_JAL Cxq_ '400RRECTTION CANNOT BE iV_DE '

$,_ITI-Ilq_iS OFTION.',/,IX,'RESET VIRTIJAL ORIGIN OPTION ?')

READ( IiN,130, ERR=2! 6,END= 9999)ANS

IF (A_S. EQ. IHY)W(29) =C.O

2'8 CX]_ITINUE

"20 WRITE(IOUT, I 25)

READ( IIN,130,ERR=220,END= 9999)ANS

IF(ANS. EQ. IHY)GO TO 10

GO TO I000

TIRANSITION OPTION 3

WRITE(IOdT,305)

FORMAT(//,IX,'3. REYNOLDS NO. DEPENDENT',//,IOX,

¢ 'RE=LOCAL REYNOLDS NO. FOR FLAT PLATE OFFIONS',/,IOX,

$ 'RE=(RE-INF)D FOR SWEFq" CYLINDER OP'FIONS',/,IX,

$ 'HIGHEST LAMINNR RE ?')

READ (IIN,*,ERR=300, END=9999) W (14)

310 WRITE (IOUT,315)

315 FORMAT( IX, 'LOWEST TURBULENT RE ?')

READ( IIN, *,ERR=31 O,END=9999) W(20)

320 WRITE( lOUT, 125)

READ (I IN, 130, ERR=3 20, END= :)999)AN S

IF(ANS. EQ. IHY)30 TO 10

GO TO I000

C

4O0

405

C

5OO

5O5

TRANSITION OPTION 4

DEPENDENT' ,//, IX,

WRITE (IOUT, 405)

FORMAT(/I, IX, '4. RE-TNETA

$ 'HIGHEST LAMINAR VALUE ?')

READ( IIN,% ERR=-4DO,END=9999) W(14)

410 WRITE(IOUT,415)

415 FORMAT( IX, 'LOWEST TURBULENT VALUE ?')

READ( I IN,_,ERR=-41O,END=9999) W(20)

420 WRITE( lOUT, 125)

READ (IIN, 130, ERR=-420,END=9999) ANS

IF(ANS.EQ.IHY)GO TO 10

GO TO 1000

-- TR/_"SITION OPTION 5

WRITE(lOUT,505)

FORMAT(//,1X,'5. PlDAC-E TRANSITION: RE-THETA/',

$ '(ME*(I_'IO*V/MU)**.2) ',//,IX,

$ 'HIGHEST LAMINAR VALUE ?')

RE/_)(I IN,% ERR=-500,END=9999)W(14)

510 WRITE( IOUT,515)

515 FORMAT( IX, 'LOWEST ll_RSULENT VALUE ?')

RE/_](IIN, *,ERR=51 O,END=9999) W(20)

520 WRITE( lOUT, 125)

READ( IiN,130, ERR=52G,END=9999) ANS

IF(ANS. EQ.IHY)GO TO 10

ORIC_NAL PAGE Ig

OF POOR QUALITY

C-40
O

6OO

6O5

610

C

7O0

705

710

C

8O0

805

810

815

e2o

C

9O0

910

1000

9999

GO TO 1000

TRANSITION OPTION 6

WRITE(lOUT,605)

FORMAT(//,IX,'6. MDAC-E T_LE LOOK-UP',II,IX,

$ 'oFrrlONAL INPUT: (L)FULLY TURIB/(L)TRAN ONSET',

$ /,IX,'***** INPUT THE RATIO OR 0.0 ***_t',/,1X,

$ tlNP1JT DESIRED ?')

READ(IIN,*,ERR=609,END=9999)W(28)

WRITE(lOUT, 125)

READ(IIN, 130,ERR=610, END=9999)ANS

IF(ANS.EQ.1HY)GX] TO 10

GO TO I000

TRANSITION OPTION 7

WRITE( lOUT,705)

FORMAT'//,IX,'7. NAR RE VS. _ TABLE LOOK-UP',

$ //,IX,'NO INPUT REQUIRED')

WRITE( IOUT, 125)

READ( IIN,130, ERR=71 O,END=9999)ANS

IF(ANS.EQ.IHY)G<) TO 10

GO TO I000

TRANSITION OFTFION 8

WRITE( lOUT,805)

FORMAT(//,IX, '8. RE-T]-IETA/ME DEPENDENT' ,//,I X,

$ 'HIGHEST LAMINAR VALUE ?')

READ( IIN,_,ERR=800, END=9999) W(14)

WRITE(IOUT,815)

FORMAT( IX, 'LOWEST TURBULENT VALUE ?')

READ( IIN,i,ERR=81 O,END=9999)W(20)

WRITE( lOUT, 125)

READ( IIN,130, ERR=820, END=9999)ANS

IF(ANS.EQ. IHY)GO TO 10

GO TO I000

BAD OPT ION

CONTINUE

WRITE(lOUT,910)

FORMAT(//,1X, 'BAD Or'F ION NU!_ER' ,//)

GO TO 10

CONTINUE

RETURN

C_NT INUE

CALL EXIT

END

OF-,--

._. , _

QUA LITY

C-41
q

C

C

C

SUBROUTINE W N(]TUN OF P®R QdAL'.I'Y

ROUTINE FOR INPUTING ATNK)SF'HERIC DATA FOR WIND TUNNEL OF'TtON

COI,4NK}N/WA_RRA,Y/W ( "/O0 )

COMMC)N/UN IT/I I N, lOUT

COMtvION/MI SC/NC, JFKS, TFL A/_;, _FL AG-, ANS1

INTEGER ANS, TFLAG,ANSI

NPTS : NjIVlBER OF TIME DEPENDEhT TA_LE E_CTT_rES

M.AY USE DATA FROM PREVIOJS CASE IF JcKS -: I OR 3

IF(jFKS.NE _.A_9.j_K_ N_ _SO _ 9

N_! =NC-!

I W_ITE (iOUT_ 2 )NC, NC_!

2 FORI_,aT(IHI,' IS CASE 't 13,' WIND TLNNEL DATA SA_qE AS 'J

$ 'FOR CASE ',13,' ?')

READ(IIN, 80,ERR=I,END=99_9)ANS

IF(ANS. EQ. 1HY)RETURN

9 CONTINUE

NI=TS=W (,50 )+.0901

10 WR ITE (IGUT, 20) NFq'S

20 FORY,_T(///,' WIND TUNNEL OPTION',//,

$ ' INPUT STATIC TEMPERATURE AND PRESSURE /kS A FUNCTION ',

$ 'OF TIME.',/,' TIME AND FREESTRENvI VEL. ARE INPUT ',

$ 'IN TRAJ. D,_TA WITH ALT. SET = O.O',/,IX

$ 6(' -'),12, _ V,A&UES REQUIRED',6(' -'),/)

IF (MFLAO.EQ.O)WRITE( lOUT, 30)

IF (MFLAG. EQ.I )WRITE( iOUT,31 )

30 FORMAT( IX, 'T-I NF (R) ,P- !NF(LB/SFT) ')

31 FORIVIAT(IX, 'T- INF (K), P- INF (NEWTON/SQ. M) ')

DO I000 I=I,NI=TS

_I0 WRITE(lOUT,50) I

50 FORMAT( IX, 12)

READ( IIN, *, ERR=4O,END=9999) w' _.50+I),W(SCO+i )

I000 CONTINUE

60 WRITE (lOUT,70)

70 FORM_T(_X,'AIRE ALL INPUTS OORREC'T ?')

READ( IIN,80,ERR=60,END=9999)ANS

80 FORMAT(AI )

IF(ANS.EQ, IHN)GO TO 10

RETdRN

9999 CONTINUE

CALL EXIT

END

C-42
C

C

I000

C

1

2

4

SUBROUTINE UNITS

ROUTINE FOR CONVERTING TO IvETT_ICUNITS

CCmlES WORKING ARRAY W INTO GUTI_JT ARRAY

OD_N/_ARRAY/W (700 )

COMMON/WWAR AY/WW (70] )

CO_54DN/WWW_LRY/WWW(700 )

COMI_IDN/UNIT/IIN, IOUT

COM_I_)N/I@_SC/_K_,JrKS,TrL _, MFL_G, A_S _

INTEGER TFL_,ANS!

2000

DO 1000 I=I,700

WWW(1)=WW(1)

WW(1)=W(1)

CONTINUE

MFLAG = 0 ENGLISH UNITS

IF(MFLAG.EQ.O)GO TO 2000

WW(12)=W(12)*3.28084

WW(13)=W(13)*3.28634

WW(22)=W(22)*3.28084

WW(25) =W(25) *3.28084

WW (20 2)=W (202) *3.28084

WW( 2C 5)=W (205) *3.28084

WW(354)=W(354)*3.28084

DO ! I=571,580

WW(I )=W(I )*3.28084

DO 2 I=I01,200

WW(I )=W(I )'3.28084

DO 3 I=401,450

WW(1)=W(1)*3.28084

DO 4 I=451,500

WW(1)=W(1)*I.8

DO 5 I=501,550

WW(1)=W(i)*O.0208855

WW(316)=W(316)*8.81143E-5

WW(21)=W(21)*4.30189E-4

WW(24)=(W(24)*1.8-459.7)

CONTINUE

RETURN

END

WW

C-43
C

C

C

C

SUBROUTINE ObTPUT

ROUTINETOCREATEINPJTFILE FORLANMIN

FNANI4- OUTPUTF!LE_AME(INPUTFILE FOR

COIVhVl0 N/_ARRAY/W(70O)

COM@IO N/'W)_, ARA'r/)))_,(700)

COMIAON/W_A_Y/WWW (_'0u) r

C0;-_'4C_/UNIT/_ IN, IOUT

COM_C.N/PP:EFF/T_C_( 50), TCP_(5C) ,NCP _-,q

COM'_N/_ _SC/NC, JFKS, T_ L_, _FL AS, A_ $I

C0'4._C,N/._TP'-'',,,' S"'_ u, '4UC

LAN_,! N)

i_,TEGER AJ_S,:FLAG, ANSI

Cl_/kRACT ER*20 FN AMz.

C_AR,A.SZTER*72TITLI

r !MENSiON IS(5)

C

IF(_.GT.I.0)GO TO 26

C 0STAIN OUTPUT FILE NKUlE /V4D OPEN

IO WRI TE(IOUT,20)

20 FORMAT(IHI,10X,'CREAT_ OUTPUT FILE',//,IX,

$ 'WHAT IS THE NAME OF THE OUTPUT FILE TO BE CREATED ?')

PEAD (f IN,25,ERP= I0,END= 9999) FNAM4

OPEN(UNIT=B,FILE=FNA_I4,STATUS='NEW',ERR=-B 88)

25 FOR_'_T(/k20)

C WRIIT_ DATA TO OUT._JT FILE ACX]XDRDINGTO PP,0GP.AMINF,.ITOONTROL

C PAR/V_ETER OF PREV IOUS CASE

26 CX_)}'4T lNUE

IF(JFKS.NE.0),CO TO (100,9999,}0,30,100,30) ,JFKS

30 IF(TFLAG.NE.I)G<) TO 33

WRITE( IOUT,31 )NC

31 FOR_#_T(IX,'_,' YOU WISH TO O_A.NGE T_4E TITLE FOR CASE ',13,_

RE_{I IN,32, ER_=30, END=999cj,'AN S

:52 !:OR,V, AT ( AI )

I¢(ANS.EQ. IUN)GC TO 52

33 WRITE(IOUT,40) NC

40 FO_J,;AT(/,IX,'WHAT IS TI_E TITLE FOR CASE 'o13,' ? ',5X,

$ '(._O'rE• 72 CHAR. LIMIT)')

RE&D( _iN,50, ERR=33, E_ID=9999)T ITLI

50 FORMAT (A72)

C TITLE --_

52 WRITE (8,55)TITLI

55 FOR_'F (A72)

C TIMING PAR/V4ZTERS AND

WRITE (_,6G) (WW(I), I=I_6)

60 FORMAT [3F20.3 )

IF(JFKS.EQ.3.0R. JFKS.EQ.6)GO TO 100

C ............ N_ER OF TIME DEPENDENT

WRITE (8,70)WW(50)

70 FORMAT (3F20.5,2F I0.3 )

N=WW(5C)+.O01

NT=50-N

C

PR INT CX)NT#OL ....

TR_ T/I_BLEENTRIES --

TR _ DATA

C-,44
C

C IF

1O0

110

120

C

130

8O

81

82

C

200

C

25O

C

300

90

95

WRITE (8,70) (WW(K), WW(K+50), WW(K+ 100) ,WW(K+160), WW(K+600),

$ K=51 ,NT)

............... CASE DATA

IZFLAG = I THEN THE ZERO VALUE FOR THE W MUST BE PRINTED

J=9

J5=I

IF(JS.GT.5)GO TO 130

IZ FLAG=O

F (J.GT.49.AND. J.LT.20! )J=201

F(J.GT.210.AND. J.LT.261 )J=26!

F(J.ST.7OO)GO TO 200

F(J.EQ.641 )J=J+1

F (WW( J ).EQ.O .0.AND. WWW( J ).NE.O .0) IZFL AC,=I

F(WW(J) .NE.O.O.OR. IZFL_.EQ. I )IS(JS)=J

F(J.EQ.649.N_D.WW(J).GT.O.O)C_K) TO 300

IF(WW(J).GT.IOOO.O.OR.WW(J).LT.I .O.AND.WW(J),GT.O.O)GO TO 400

IF(WW(J) .NE.O.O. )R.IZFLN_.EQ.I )"S=JS+I

J=J+l

GOTO 120

WRITE CASE DATA TO OtdTPUT FILE

WRITE(8,80) (IS(K),WW( I S(K) ),K=I ,5)

FORP4AT(5( 13,F9.4, lX) )

FCHRMAT(5 ( 13,F9.7, ; X) )

FORMAT(5(13,F9.1,1X))

GO TO 110

WRITE PROGPJ_M INPIJ"rCONTROL PARAMETERS FOR CASE ---

IS(JS)=641

WRITE(B,80) (IS(K),WW(IS(K)),<=1, JS)

(3-1EC_FC_ STREAMLINE C._SES

IF(ISTRM.EQ.I)GO TO 500

CONT INUE

IF(INSERT.EQ.O)JFKS=WW(641 )+.0001

F ( JF_'S .EQ. 2 )_OSE (UN I1 =B)

RETURN

PRESSUPE COEFFICIENT INPUT T/W_LES ---

CONTINUE

WRITE (8,80) ( ! S(K),WW(!S(K) ),K=I ,JS)

WR lTE (8,90) NCPMT

FORMAT (I3 )

WRITE (8,95) (TMC,P(K),TCPM(K),K=I ,NCPM'F)

FORMAT (2F I0.6)

J=J+l

GO TO 1_0

OPTIONAL FORMAT FOR WRITING CASE DATA TO OUTPUT FILE ......

CONT I NUE

IF(JS-1 .C___.1)WRITE(B,80) (IS(K),WW( IS(K)),K=I ,JS-1 )

IF(WW(J).LT. 1000.)WRITE(8,81 ) J,WW(J)

I F (WW(J) .GE. 1000. ) WRITE (8,82) J, WW(J)

J=J+l

GO TO '10

COPY STREAMLINE CASES FROM TENPORARY STREAMLINE FILE --

CONT I NUE

RE/U)(4,80)Jl,W(Jl ), J2,W(J2), J3,W(J3), J4,W(J4), JS,W(JS)

READ (4,80) J6,W( J6 )

WRITE(8,80) J1,W(J1 ),J2,W(J2), J31W(J3), J4,W(J4), J5,W(JS)

C-45
IF(W(JI ).EQ.NNC-I )GO TO 510

WRITE (8,80) J6,W(J6)

GO TO 500

C O-ICK)SE PROGRAM INPUT CONTROL PARAMETER FOR LAST STREAMLINE CASE

510 CONTINUE

WRITE ( IOUT, 520)

520 FORMAT(//,lr.,x,'INPUT CONTROL FLAG',//,

$ 1X,'t. NEW _'ASE FOLLOWS US'NG TITLE,TIMING AND TRAJ. ',

$ /,6X,'DATA FROM PREVIOUS CASE',/,

$ IX,'2. END OF INPUT (LAST CASE)',/,

$ IX,'3. NEW CASE FOLLOWS USI_ T_AJ.DATA FROM PREVIOUS ',

$ 'CASE.' /,6X,'NEW TITLE AND TIMING. INITIAL CASE DATA '

$ 'UNCHANGED.',/,

$ IX,'4. NEW CASE FOLLOI_S USING _JEW TITLE, TIMING,TIRAJ. ',

$ 'AND CASE DATA.',/,6X,'(INiTIAJ_LY ZERO W #JR,RAY),,/,

$ IX,'5. SNwIE AS (I) EXCEPT ZERO ALL CASE DATA FROM ',

$ 'PREVIOUS CASE',/,

$ IX,,6. SAME #.5 (3) EXCEFT INITIALIZE ZERO ALL TIMING ',

$ 'AND CASE DATA',//,

$ IX,'OPTION SELECTED ?')

READ( I!.k,,,ERR=510, END=9999)W(j6)

WRITE _8,80) J6,W(J6)

CLOSE (UN IT=4, STATUS= 'DELETE' )

NC=W( 647 )+.0001

GO TO 250

8888 CONTINUE

WRITE (IOUT, 8889 )FNAN$4

8889 FORMAT(/,IX,'CANNOT OPEN ',/k20,/)

GO TO 10

9999 CONT 1NUE

CALL EXIT

END

oRIGiNAL FACt !_

OF pOOR QUALITY

C-46