-space shuttle- static aerodynamic …-space shuttle-static aerodynamic characteristics for the gac...

DMS-DR-1161 AUGUST 1971

-SPACE SHUTTLE-STATIC AERODYNAMIC

CHARACTERISTICS FOR THE GAC ROS-NBI AND ROS-WBI ORBITER CONFIGURATIONS AT TRANSONIC

MACH NUMBERS [M=07-116)

by FManke GAC RKrepski GAC

bullB Johannesen GAC

i

Sgt-i90 (NASUUMER)26

S-__

Z GRUMMAN FARMINGDALE INCH TRANSONIC WIND TUNNEL

SADSAC SPACE SHUTTLE AEROTH ERMODYNAMCG

DATA MANAGEMENT SYSTEM

GRUMMAN AIRCRAFT

CORPORATION

CONTRACT NASS-4016

MARSHALL SPACE FLIGHT CENTER

secvsl C14RYSLERST SPACE DIVISION Q CR AI

797

httpsntrsnasagovsearchjspR=19710029193 2020-03-11T211947+0000Z

NASA Series Number S-0607 DM5-DR-11 6 1 AUGUST 1971

SADSACSPACE SHUTTLE

WIND TUNNEL TEST DATA REPORT

CONFIGURATION Grumman Configuration ROS-NB1 and ROS-WB1

TEST PURPOSE Determine basic transonic force data for two delta wing

orbiter configurations (M = 07 - 116)

TEST FACILITY Grumman Farmingdale 26 transonic tunnel

TESTING AGENCY Grumman Aerospace Corporation

TEST NO amp DATE GFTT - 035 31771 to 42171

FACILITY COORDINATOR M Quan GAC

PROJECT ENGINEER(S) F Manke GAC

R Krepski GAC

B Johannesen GAC

DATA MANAGEMENT SERVICES

LIAISON L~_DATA OPERATIONSjoanl Z vaugn a4

RELEASE APPROVAL 1p DbullKemp upervisor

Aero Therme-Wata Group

CONTRACT NAS 8-4o6 AMENDMENT 153 DRL 184 - 58

This report has been prepared by Chrysler Corporation Space Division under a Data Management Contract to the NASA Chrysler assumes no responsibility for the data presented herein other than its display characteristics

FACILITY COORDINATOR

Mr M Quan Grumman Aerospace Corp Bethpage Long Island New York 11714

Phone (516) 575-7o44

PROJECT ENGINEERS

Mr F Manke Mr R Krepski Grumman Aerospace Corp Grumman Aerospace Corp Bethpage Long Island New York 11714 Bethpage Long Island New York 11714

Phone (516) 575-7044 Phone (516) 575-7044

Mr B Johannesen Grumman Aerospace Corp Bethpage Long Island New York 11714

Phone (516) 575-7044

SADSAC LIAISON SADSAC OPERATIONS

Mr J E Vaughn Mr J R Ziler Chrysler Corp Space Division Chrysler Corp Space Division 102 Wynn Drive P 0 Box 29200 Huntsville Alabama 35805 New Orleans Louisiana 70129

Phone (205) 895-1560 Phone (504) 255-2304

ABSTRACT

Two 1200 scale models of the Grumman ROS-NB1 and ROS-WBl space shuttles

were tested in the GAC 26 inch Transonic Wind Tunnel in Farmingdale 1ew

York Mach number was varied from 7 to 115 Model angle of attack was

varied from -3 to 13 at 0 sideslip Sideslip angle was varied from -20 to

100 at set angles of attack of 00 and l00 Date were taken during a sweep at

approximately every 7

Two different basic configurations were tested the narrow body ROS-NB1

and the wide body ROS-WB1 Test configurations included a model build-up

body alone body-wing and body-wing-tail Symmetric elevon deflections were

tested to determine longitudinal control effectiveness The effect of the

rudder wing tip fins and an auxiliary ventral fin was also determined

All testing was conducted without transition

NW19 = XTIVROTZMHI HIV(l SIM

TABLE OF CONTENTS

PAGE NUMBER

LIST OF FIGURES AND TABLES 2

SUMMARY 3

CONFIGURATIONS INVESTIGATED 4

DATASET COLLATIONS 5

TEST FACILITY DESCRIPTION 6

TEST CONDITIONS 7

DATA REDUCTION 8

SUMMARY DATA PLOT INDEX 10

FIGURES 12

MODEL COMPONENT DESCRIPTION SHEETS 19

GENERAL NOMENCLATURE 28

TABULATED DATA LISTING 33

PLOTTED DATA 34

1~

LIST OF FIGURES

FIGURE PAGE NUMBR TITLE NUMBER

1 Axis System 13

2 Installation Photograph of GAC 14 Configuration RCS-NB1

3 Three-View Shetch - Configuration 15 ROS-NB1

4 Three-View Sketch - Configuration 16 ROS -WBI

5 W2 - Wing 17

6 U1 - Ventral Fin 18

LIST OF TABLES

TABLE PAGE NUMBER TITLE NUMBER

I SADSAC Nomenclature of Aerodynamic 9 Coefficients

2

SUMMARY

This report presents the details end results of the first series of

transonic tests conducted on 1200 scale models of the Grumman Aerospace

ROS-NB1 and ROS-WB1 orbiter vehicles in the Grumman Farmingdale 26 Transhy

sonic Tunnel The period of occupancy was from March 17 to April 21 1971

on a one shift per day basis

Additional tests were conducted on these same models in other Grumman

facilities to more fully cover the Mach number range This series of tests

are covered in the following reports

SADSAC Report Number Mach No Range

Ems-DR-1081 017

DmS-DR-1161 07 to 115

TXAS-DR-1163 20 and 25

DMS-DR-1159 100

Six component aerodynamic force and moment coefficient data are preshy

sented herein in plotted form and cover an angle of attack range from -30

to 130 at zero degrees sideslip and -20 to 100 sideslip at 00 and 100 angle

of attack

3

CONFIGURATIONS INVESTIGATED

The following model components were tested

BI - basic ROS NB1 fuselage

B2 - ROB WBI fuselage which is wider than -NBI

W1 - basic ROS NB1 wing

W2 same wing as W1 except tips have been clipped

V1 - single vertical tall for ROS NB1

V2 - twin vertical tails for ROS WB1

V3 - tip fins for wing W2

U1 - basic ventral fin mounted to body flap when body flap is at 00

Pertinent dimensional Information for each of these components is given in the

section entitled Model Component Description Sheets Sketches of the components

are shown in Figures 3 through 6 The Data Set Collation Sheet which follows immediately

contains a summary of the test run schedule and configurations tested

4

TEST GFTT-035 DATA SET COLLATION SHEET J

A5i1C T-At5j tIC AERODMA4 I( PIAA OM TOO 20 SCALE DPRETEST

Mo40csVE OF TC- ampQ AO MAK bs-tsBk1 AMD fZOS-t l OBIB]ERS M POSTTEST DATA SET SCHD CONTROL DEFLECTIO NO ACH NUMBERS

IDENTIFIER CONFIGURATION of - - _

I -p RUNS 7 s 9 95 1-RCPgz 31 WV A 0 00o 5 0 29 23 252 RcRoZ8 WiV 0 B 0 0 0 8 29 30

CZ-o3 B WV 0 B o0 0 S 3i~ 2 33 Ceo35 Bi~L l A O -10-ioo 3 35 -amp 38

RO4I A - -5 o plusmn 59 40 c--IO_______t V 2o-o a -- - 4(

PCPo42 1WWV A 0 o to 3 42 43 44 PClro4 wvvoV 0 B 0 0 0 4

RCP-0o4 _jQ 8 B 00 shy 3 44 47 -5

RCR049 BVwplusmnV 061 0 0 0 - 2 9 50 RcROSI 13 A 0 -- - s51 52 53 kCP055 B2UWY A O 0 o o 51 57-55r

gc05g B2W Vplusmn o 5 0 0 0 3 58 3 - _

pzcfot) 32kJ VL 1o 3 o 0 o 61 2iZCcL B)W osA 0 amp40 3 ZCP-oGo TN 0C O o 3 44] 44

_shy

CcaOG7~J 05 B367 0 49 69

1 7 3 19 25 31 - 37 943 55 61 67 7576

COEFFICIENTS __________(________ ____(_) ___DV -___ a or a oltq = -I o A(7 o l

SCHEDULES 1 deg o o e y48 -z 0 Ia(oon a or creuro 7deg

TEST FACILITY DESCRIPTION

GRUNMAN 26-INCH TRANSONIC WIND TUNNEL

DESCRIPTION This is an intermittent blodown to atmosphere type facility

The slotted test section is octagonal measuring 26 inches across the flats

The Mach number is controlled by a sliding gate valve downstream of the

section

P)RFMANC E PARAIMTERS

Mach Range o6 to 13

6 Reynolds Number (x 10 ft) 7 to 29

Stagnation Pressure (psia) 25 to 75

Dynamic pressure (psf) 835 to 4600

Stagnation Temperature (OR) 46o

Run Time (seconds) 20 to 46

TESTING CAPABILITIES This tunnel was intended primarily for flutter tests

although it also is suitable for general aerodynamic testing This facility

is equipped with a computer controlled Data Acquisition System

6

TEST CONDITIONS TEST G~ry o45

REYNOLDS NUMBER DYNAMIC PRESSURE STAGNATION TEMPERATURE MACH NUMBER per unit length (poundssq inch) (degrees Fahrenheit)

deg 7 73 x 1O6 620 30

1068 79 x 741- 30 308299 83 x 1o6

bull 86 x lo6 868 300

300996115 87 x lo6

BALANCE UTILIZED TASK 75 MK XLIII A

COEFFICIENT

CAPACITY ACCURACY TOLERANCE NF 200 lb +486 0039 SF 200 b T759 0063

AF 80 1b 7L2T 0 PM 300 _-357In-ib 0003

M 125 in-ib -192A 0013 207 0003R4 80 in-lb

COMMENTS

7

DATA REDUCTION

The 075 inch TASK MK XLII six component strain gage balance was used to

measure orbiter forces and m3oments All final data were presented along and about

the stability axis passing thirough a nominal center of gravity located at F S 1485 (7 425

model scale) W L 377 (1 885 model scale) and B L 0 Data were converted to stanshy

dard NASA coefficients using the following constants (model scale)

reference area Sref = 20 689 sq in =wing W1 planform area

reference length 1ref = 9 648 in = body length

reference span bref = 5 838 in = wing W1 span

No adjustment to the final data was made to account for the base and cavity

pressure contributions

8

TABLE I SADSAC NOMENCLATURE OF AERODYNAMIC COEFFICIENTS

SADSAC NOMENCLATUI

COEFFICIENT

CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME

Total Axial Force Base Axial FQrqe Forebody Axial Force

Total Drag Force Base Drag Force Forebody Drag Force

Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment

Lift-To-Drag Force Ratio

Lift-To-Forebody Drag Force Ratio

Normal-To-Axial Force Ratio

Normal-To-Forebody Axial Force Ratio

BODY AXIS

CA CAB CAF

---

-

CN

CY

CBL

CLM

CYN

NA

CNCAF

STABILITY AXIS WIND AXaS

-shy

- -

CD CDTOTL CDB CDBASE CDF CDFORE

CL CL

- -

CY CC

CSL CWL

CLM CPM

CLN CLN

LD CLCD

LDF CLCDF

- -

- -

SUMMARY DATA PLOT INDEX

PLOT TITLE

Characteristics in Pitch Narrow Body Orbiter

-

PLOTJYTED COEFFICIENTS

SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116

NOMINAL a SCHEDULE (DEGREES)

-3 - 13

NOMINAL SCHEDULE (DEGREES)

0

PAGES

1-5

Characteristics in Pitch Narrow Body OrbiterII

- B Configuration 07-116 -3 - 13 0 6-15

Elevon Effectiveness Narrow Body Orbiter

--

A Elevon Deflec-tion Angle

07-116 -3 - 13 0 16-18


- B Elevon Deflec-tion Angle

07-116 -3 - 13 0 19-24

Rudder Effectiveness Narrow Body Orbiter

- C Rudder Deflec-tion Angle

07-116 -3 - 13 0 25-33

Characteristics In Sideslip -

Narrow Body Orbiter - (ALPHA = 0)

D Configuration 07-116 0 -4 - 12 34-42


Narrow Body Orbiter (ALPHA = 10) D Mach Number 07-116 10 -2 - 11 43-45

Characteristics In Pitch -Wide Body Orbiter

A Configuration 07-116 -4 - 12 0 46-48

Characteristics In Pitch Wide Body Orbiter

- B Configuration 07-116 -4 -- 12 0 49-54


Wide Body Orbiter (ALPHA = 0) D Configuration b7-i16 0 -4 12 55-63

SUMMARY DATA PLOT INDEX (coNTNUED)

PLOT TITLE

PLOTTED COEFFICIENTS

SCHEDULE CONDITIONS VARYING

NOMINAL MACH

NUMBER


NMINAL SCHEDULE (DEGREES) PAGES

Characteristics In Sideslip -Wide Body Orbiter (ALPHN = 1O)

D Mach Number 07-116 10 -2 - l 64-66

Longitudinal Characteristics -Narrow and Wide Body Configushyrations

E Configuration 07-i16 plusmn5 0 67-69

Lateral-Directional Characteris-tics - Narrow and Wide Body Conshyfiguration (ALPHA = 0)

F Configuration 07-116 0 -5 - 5 70-72

Lateral-Directional Characteris-tics - Narrow and Wide Body Conshyfiguration (ALPHA = 1O)

F Configuration 07-116 10 -5 - 5 73-75

PLOTTED COEFFICIENTS SCHEDULE

SCHEDULE A SCHEDULE B SCHEDULE C

CL vs a CL CL

vs vs

CD CIM

CUN CSL CY

vs vs vs

a a a

SCHEDULE D SCHEDULE E SCHEDULE F

cIN CSL c

vs vs vs

P P P

d(CL) vs d(CIMCL) vs

CD(MIN) vs

MACH No MACH No MACH No

d(CN) d(CSL)

d(C)

vs vs vs


FIGURES

12

Notes 1 Positive directions of force coefficients

moment coefficients and angles are indicated by arrows

2 For clarity origins of wind and stability axes nave been displaced from the center of gravity

IZ

ZW

CLL

Faire 1 Axis systems sitowitig direction and sense off force andmoment coefficients angle of attack and sideslip angle

NA$A-MSFC-AAF

I

4H 4

0 flgure 2 Installation Photograph of GAIC Configuration flO8-NB1

4-r REPCPDiVCC CMFA(SION S

Si = 6747 FT 0QrEc 1608 prX

V- 973 FT

rs- 200

LI- FS 1485 it

_l f 1 -fS0

z

Figue 3Three View Sketch-Configuratlou ROS-NB1

REFEPENCE DIIENSON5

Spay-747 rlTL x

XF 1608 pr

6 Frr

FS 200

z

Figure 4 Three View Sketch-Configuration RO6-WBI

Basic W wing clipped to accomadate V3 wing tip fins Ref drawing

518 MOD 802

-W

W

leicent- 4609

FIGURE 5 VA WING tFuLL SCALE

0

U- VENTRAL FiN

(X2oo SCALE)

H 425

-

SEC-T A- A Figure 6 U1-Ventral Fin

MODEL COMPONENT DESCRIPTION SHEETS

19

MODEL COMPONENT BODY - B1

GENERAL DESCRIPTION BASIC ROS-NB1 BI

DRAWING NUMBER 518 MOD 900 1200

DIMENSIONS FULL-SCALE MODEL SCALE

(FT or FT2) (in or in2 )

Length i608 9648

Max Width 280 168o

Max Depth 287 1722

Fineness Ratio 3 61

Area

Max Cross-Sectional 6-6 2218

Planform 990 14364

Wetted i 6-y 45396

Base 59r 2124

20


GENERAL DESCRIPTION BASIC ROS-TIBI Bony

DRAWING NUMBER 538 man (o-

DIMENSIONS FULL-SCALE 0

MODa ScALE

Length (rr OR n2)a6o8

(INOR IN 2 ) 9648

Max Width 448 -2fa

Max Depth 288 17PR

Fineness Ratio 36 16

Area

Max Cross-Sectional 956 442

Planform 516o

Wetted f2 47-628

Base 7- 2678

21

MODEL COMPONENT WING - w

GENERAL DESCRIFFION BASIC ROS-IB I WING

DRAWING NUMBER 518 n P 1200


TOTAL DATA (I OR Fr2) (IN OR IN2 )

Area Planform Wetted A P8oo8

Span (equivalent) 973 58R Aspect Ratio -z65 Rate of Taper 187 -87 Taper Ratio Diehedral Angle degrees Incidehce Angle degrees +

-129 0o0

odY -3 tip

IP9

Aerodynamic Twist degrees Toe-In Angle Cant Angle Sweep Back Angles degrees

Leading Edge 60 deg 60 deg

Trailing Edge 025 Element Line

T2-90 Z2a U

Chords Root (Wing Sta 00) Tip (equivalent)

i046 135

6P76 81o

MAC 590 95o Fus Sta of 25 MAC Z5UO inn 90 WP of 25 MAC 3026 1 BL of 25 MAC

Airfoil Section Root 18 maxcamber 10 thickness Tip Smaxaber plusmn0 thickness

EXPOSED DATA

Area 3217 11-81

Span (equivalent) 693 I8 Aspect Ratio 15 15 Taper Ratio 172 172

Chords Root 7825 4 Tip 3 81 MAC __4 2784 Fus Sta of 25 MAC WP of 25 MAC BL of 25 MAC

22

MODEL COMPONENT Elevon (For the W Wing)

GENERAL DESCRIPTION Moveable Control Surface Associated With the W Wing

DRAWING NUMBER 518mogo

DIMENSIONS

Area

FULL-SCAL (ft or ft-)

364

1200 MODEL SCALE (in or in)

110

Span (equivalent) 355 2110

1chord 1275 T65

Outbd equivalent chord 775 465

Ratio Elevator chordhorizontal tail chord

At Inbd equiv chord

At Outbd equiv chord

Sweep Back Angles degrees

deg 0 00Leading Edge

Tailing Edge 8

Hingeline

Area Moment (Normal to hinge line)

23

MODEL COMPONENT VERTICAL TAIL - Vl

GENERAL DESCRIPTION BASIC ROS-NB 1 VERTICAL TAIL

DRAWING NUMBER 518 MOD 902

DIMENSIONS FULL-SCALE (r OR F

MODEL SCALE (IN OR IN2 )

Area 805 2898


Inbd equivalent chord 346 2076


Ratio movable surface chordtotal surface chord

At Inbd equiv chord 3 3

At Outbd equiv chord 3


Leading Edge 450 45deg

Tailing Edge 197 deg 190

Hingeline 2870 287

Area Moment (Normal to hinge line) 945 204

AflMOIL SECTION 64Aolo 64A01o

24

NASA-MSFC-MAF

MODEL COMPONENT Rudder (for the V1 vertical tail)

GENERAL DESCRIPTION Moveoble Control Surface Assoclated With the V

Vertical Tail

DRAWING NLLMBER 518 MOD 9lt2

1200 DIMENS IONS FULL-SCAL

(ft or t-) MODEL SCALE(in or In

Area 240 864

Span (equival ent) 333 1998

chord 104 624

Outbd equivalent chord 4o2 241

Ratio evaWr chordhorizontal tail chord


At Outbd equiv chord 3 3


Leading Edge 295 2950

Tailing Edge 19970170

Hingelne

Area Moment (Nornal to hinge line)

MODEL COMPONENT TWIN BODY TAILS - V0

GENERAL DESCRIPTION BASIC ROS-VJB1 VERTICAL TAILS


DIMENSIONS

Area

Span (equivalent)

Inbd equivalent chord

Outbd equivalent chord

Ratio movable surface chord total surface chord

At Inbd equiv chord



Leading Edge

Tailing Edge

Hingeline


AIRFOIL SECTION

CAT ANGLE (OUTBOARD)

MODEL SCALE (IN OR IN)

2rop

1990

534

400

85deg

NAA 64A010

150

NASA-MISFC-MAI

FULL-SCALE (I OR d)

670

5521

3317

908

400

85 deg

NAcA 64Ao1

150

26

MODEL COMPONENT WING TIP FINS - V3

GENERAL DESCRIPTION VERTICAL FINS IOCATED AT T E TIPS OF THE CLIPPED

BASIC WING (DESIGNATED W2)

DRAWING NUMBER


Area CPT oR I)

684 (INcen TN) 2462


Inbd equivalent chord 3025

Outbd equivalent chord 1517 1o


At Inbd equiv chord T274 274




Tailing Edge i8440 1844P

Hingeline 18410 18440


CANT ANGIE 5P(OUBOARn) s deg (OUTsOnD)

deg 100TOE-IN ANGLE 10

27

NCMENCLA

(Genera

SADSAC SYMBOL SYMBOL DEFINITIC

a ALPHA angle of attack angle between the projection of the wind Xw-axison the body X Z-plane and the body X-axis degrees

BETA sideslip angle angle between the wind Xw-axis and the projection of this axis on the body X-Z-plane degrees

PSI yaw angle angle of rotation about the body Z-axis positive when the positive X-axis is rotated toward the positive Y-axis degrees

PHI roll angle sngleJof rotation about the bodyX-sxis positive when the positive Y-axis is rotated toward the positive Z-axis degrees

P air density Kgm3 slugsft3

a speed of sound msea ftsec

V apeed of vehicle ielative to surrounding atmosphere Msec ftsec

q Q(PSI dynamic pressure l2P psi psf

Q(PSF)

M MACH Mach number Va

RNL RNL Reynolds number per unit length millionft

p static pressure psi

p total pressure psi

CP pressure coefficient (p-po)q

28

NOEDCLAflZ (Continued)

Reference amp C G Definitions

SADSAC

SYMBOL

S

S

SYMBOL

SREF

DEFINITION

wing area m2 ft2

reference area m2 ft 2

wing mean aerodynamic chord or reference chord m ft in

ref LREF reference length m ft in

bref

Ab

dwing span or reference span m ft in

base area 2 ft2 in2

C g center of gravity

MRP 1RP abbreviation for moment reference point

XMRP abbreviation for moment reference point on X-axis

MRP abbreviation for moment reference point on Y-axis

2MRP abbreviation for moment reference point on Z-axis

2g

NOMENCLATURE (Continued)

Axis System General

SYMBOL DEFINITION

F force F lbs

M moment M in-lb

Subscript Definition

N normal force

A axial force

L lift force

D drag force

Y force or moment about the Y axis

z moment about the Z axis

X- moment about the X axis

a stability axis system

w wind axissystem

ref reference conditions

free stream conditions

t total conditions

b base

30

SADSAC SD4OL SYI4BL

CL CL

CD CD

CD CDBb

CDf OF

Cm CTm

CY

Ch CIN

C CSL

LD LD

LDf LDF

NCNCIATURE (Continued)

Stability Axis System

DEFINITION

lift force coefficient FrqS

drag force coefficient FJqS

base drag coefficient

forebody drag coefficient CD - CDb

tpitching moment coefficient MysqS ref

side force coefficient FyqS

yawing moment coefficient MzsqS bref

rolling moment coefficient MXsqS bref

lift-to-drag ratio O

lift to torebody drag ratio CJCDf

31

SD4BOL SADSAC SYMBOL

it HORIZT

6

AILRV

CANARD ELLEVN ELEVMT FLAP RUDDER SPOILR TA

6

AIL-L AIL-R ELVN-L ELV-R SPLR-L SPLR-R

SURFACE

SUBSCRIPTS

0

b

c

e

f

r

ii

t

NG4UICLATWRE (Continued)

Surface Definitions

DEFlTION

horizontal toil incidence positive when trailing edge down degrees

syrcetrical surface deflection angle degrees positive deflections are

aileron - total aileron deflection (left aileron - right aileron)2 canard - trailing edge down elevon elevator

--

trailing edge down trailing edge down

flap - trailing edge dowM rudder - trailing edge to the left spoiler - trailing edge down tab - trailing edge down with respect

to coitrol surface antisymmetrical surface deflection angle degrees positive trailing edge down

left aileron - trailing edge down right aileron - trailing edge down left elevon 7- trailing edge down right elevon - trailing edge down left spoiler - trailing edge down right spoiler - trailing edge down

DEFIITION

aileron

base

canard

elevator or elevon

flap I

rudder or ruddervator

spoiler

toil

32

NASA -MSF C-MA P

TABULATIM DATA LISTING

A tabulated data listing consisting of all aero data sets both original and those created in arriving at the plotted material to be presented subseshyquently is available as an addendum to this report The tabular listing is made up in two sections

(a) a brief summary list of all data sets containing the identifier the descriptor and the resident dependent variables

(b) a full list of all data sets containing all resident or selected aerodynamic coefficients of the data sets as well as the above mentioned information

The listing is currently sent on limited distribution to the following organ-Izations

NASA AMES Mr V Stevens NASA CS Mr Ray Nelson GAC Mr M Quen

If copies of this listing are desired please contact the above or the cogshynizant SADSAC personnel who for this data is

Mr J R Ziler Department 2780 Chrysler Corporation Space Division New Orleans La 70129

(5o4) 255-2304

33

PLOTTED DATA

34

5

FIGLRE 1 CHARACTERISTICS INPITCH- NARROW BODY ORBITER

L3

a -

- 4 - 2 a 10 12 14 I

ANGLE OF ATTACK ALPHA DEGREES DATA SET 37HUM CONFIGURATION DESCRIPTION BETA ELEVNS RUDDER REFERENCE INFORMATION

IRCRU911 2 GFrT-035 euroOM ROS-N81 81MV1 0000 00DO 0000 SREF 290 3 (C01 GFtT-035 CCNF ROS-NSI I 0o000o LREF 96500 IN

BREF 583au IN XMRP 14850040 IN YRp ZRP

OOamp 310 04

IN-IN

MACH 0700 SCALE UJ5os

PAGE I

3

FIGURE 1 CHARACTERISTICS INPITCH- NARROW BOGY ORBITER

r

z

U-Lir

Ishy

-3 4 -8 0 a 4 a 8 20 2 24 to

ANGLE OF ATTACK ALPHA DEGREES DATA SET SYMBOL CONFIGURATION DESCRIPTION BETA ELEVHS RUDDER REFERENCE INFORMATION (ACROZi) (ACRSGS)

0 pound1

GFTT-035 DATA NOT

COMF ROS-NS1 AVAILABLE FOR

BIWIV1 ALL CONDITIONS

0000 000

0000 P000 SREF LREF

06900 96500

S1N IN

BREF 50380 I XNRPYhRP

4850040 0UOIO

ININ

ZpoundRP 31 004 IN MACH 0820 SCALE 00050

PAGE 2

FIGURE 1 CHARACTERISTICS INPITCH- NARROW BODY ORBITER

5

u u z

Ishya4 2 4 ait 14 i

--3 4 -2010 41

ANGLE OF ATTACK ALPHA DEGREES DATA SET SYMBOL CONFIGURATIa DE3CRIPTICN ETA ELEVIS RUDDER REFERENCE INFORMATION2PRCRO 1 GFTT-035 CCNF ROS-NBO BIWIVI 0000 0000 0000 SREF 206900 891N CRCRO51J GFTT-035 COOF RO-NBI I 01300 LREF 96500 Il

BREF 58330 1N XNRP 14050040 IN YNRP Ornfo Is

XNRP 3770004 IN ACH 0890 SCALE 0Jos

PAGE 3

FIGURE I CHARACTERISTICS INPITCH- NARROW BODY ORBITER

4

LL

t- $

- a 2_ 4_ g_ SOi 14 is

ANGLE 07 ATTACK ALPHA DEGREES Olt^ SET SYMBOL CONFIGURATION DESCRIPTION BETA ELEVNS RUDDER RFERENCE INFORMATION

0000 0000 SREF 206900 3a1m1CROR$) Q GFTI-035 CONP RO-NS1 S1wV1 0000 1RCROSI) L DATA NlOT AVAI USLE FO9 ALL CONDITION$ OOaD LREF 90500 IN

BREF 58300 1shyNRP 140040 1 YNRP 0000 IN ZIRP T7T00DO

MACH 0940 SAE 005

PAGE 4

FIGURE 1 CHARACTERISTICS INPITCH- NARROW BODY ORBITER 7 r- r----- -j--v- 1 rr-w- -r--r- -rr- r- r-r

S 3

-- Ashy

4 -2 a a at 12 4 so

ANGLE OF ATTACK ALPHA DEGREES DATA SET SYMBOL CONFIGURATIONDESC41PTION MIA ELEVN3 RUDDER REFERENCE INFORMATION

(RD5R)02)0 GFIT-035 COMF RO3-NOS BIWIVI 0O000 OGOO SREF 206900 SaIN RCR1 l OFTT-035 CONF ROS-NSI 81 DOQ EF 96500 IN

RREF 588 N XMRP 1485042 1 YmRp 202 IN

MACH $160 2MR p SC

A L E 004 00050

IN

PAGE 5

5


9 0 4 s 8 o 1 4 1 s 90 2

I-

ORAG COEFFICIENT CO DATA SET 140 CGNFIGURATICN VE5CRIFTIN SETA ELEWNS RUDDER REFERENCE INFcaNATIQft RCRS1

R 5) GFTT-035

FTT-035 CONF ROSNCCNF RO3-No

WIVI 1

QUos00D0

0000 0000 SEF LREF

Zo690096500

3QININ

BREr 5680 IN XMRP IMRP

148500 0 1

IN IN

2RP 3770004 IN MACH 070D SCALE 0oo50

PAGE 6

4


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SIOE SLIP ANGLE BETA DEGREES DATA CT YMfOL CONFIGURATION DESCRIPTION ALPHA ELEVNS RUDDER REFERENCE INFORNATION (fRCRO2) 2 GF7T-035 CONF ROc-Not SIWIVI 0000 0000 0000 SREF 2o6900 SQINCACRO46 L GFTT-035 CONF RQS-NB1 01Wa uo a00 LREF 90500 IN 1CRR4SJ DATA NOT AVAILABLE FOR ALL C-DITIONS 0000 0000 0000 BREF 50300 IN3 (RCR049) U GFTT-035 CONF ROS-NBI atIW2V3 0OOf 0000 0000 XNRP 14850040 IN

YTRP 000 SI Zh~fpt 3D004 SN

SCALE 0isoMACN 0900

PAGE 41

FIGURE 4 CHARACTERISTICS INSIDESLIP- NARROW BODY ORBITER (ALPHA= 0)10 l~m-u-n lm centI I~mw -n-I-u rr-Im u-u-r u-rn -rr rrrwrprn-1II m

A6_

u

- 2

-25

- 4 -3 -_Z 1 a 1 2 3 4 5 6 T a in 119 12 13 14

SIDE SLIP ANGLE BETA DEGREES DATA SET SYNDq CONFIGURATION DESCRIPTION ALPHA ELEVNS RUDDER REFERENCE INFORMATION

(RCRO28) Q OFTT-035 CONF ROS-N51 BlWlVl 0O000 0 D o 000 S4EF 206900 5eIN

LREF 96500 INDUD 0 00IRCRD45) GFTT-035 CONF ROS-MBI BSWIVIVI 000 000 0D SREF 5 380 IN CRCR0492[ a FTY-035 CONF ROB-NOI US NV3 GCqo 0000 0000 XNRP 01

III MCRO46) L GFTT-035 CONF RCS NBl B1

1485oQ4 1No

YRP IO IN ZMRP 37 DG04 N SCALE a deg905

MACH 1160

PAGE 42

FIGURE 5 CHARACTERISTICS INSIDESLIP- NARROW BM)IY ORBITER (ALPHA= 10]

020

C

F- 010 shy

-j

-005

z

- 015

It - 010

zLI - 025

Z 3

025 S A

SIDE SLIP ANGLE BETA DEGREES svms MACH PARAMETRIC VALUES REFERENCE INFORMATICN

RFERENCE FVLU

a2 ALPHA 10000 ELEYNS D000 SREF 206900 SQIN

SREF 0950 RUDDER 0000 LREF 965005 IN

XMRP 4IG4N YNRpZRP

000OD 004

IN

SCALE 000O1

GFTT-035 CONF ROS-NBI BIWIVI CRCR031) 10 AUG 71 PAGE 43


000

InI5

)- 005

t- 0005shy

-oZ

Iii

z

z

-4 -a3 - _ 0 4 5 6 7 a 9 10 11 1 3 14

SIDE SLIP ANGLE BETA DEGREES SYMDQ MACH PARAMETRIC VALUES REFERENCE INFDRMATION

SREF 206900 SIN o 72D ALPHA 10 Oao ELEVN $ 0000

NLREF 960 BREF Do IN

GOXR 14850040 I1

YHRpp 00000 IN ZMRP 37T0004 IN SCALE 00050

D950 RUDDER 0000

REFERENCE FILE



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I-I

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z- -05 shy

f_3VLi

Li

La

CP-A

-- HQH

SIDE SLIP ANGLE BETA DEGREES syyensC MACH FARAMEIRIC VALUES REFERENCE INFMNATIC

790 AL HA ELEVNS SLOESLIPANGL SREF 20690 8QIN10000 0000 DEA DGREE 0950 RUDDER 0000 LREF 96500 IN lg 81rF 5 83 0 IN

XNRP ao000 IN

ZHRP 3770004 IN REFERENCE FILE SCALE a0a5u

GFTT-035 CONF ROS-NBI BIWIVI CRCRO31) 10 AUG 71 PAGE 45

FIGURE 6 CHARACTERISTICS INPITCH- WIDEBOY BITER

LLI 40 bullibull

U

u

--4 2 0 2 10al 12 14 so ANGLE OF ATTACK ALPHA DEGREES

DATA SET SYMOamp CONFIGURATION DESCRIPTION BET ELEVN$ RUDDER REFERENCE INFORMATION RCRO55) 12 GFTT-035 CONF RQS-U8 92WV2 OlsoO 0O00 0000 SREF go 6900 SON RCRO) L GFTT-935 CC R03 S Sew OOO 0 000 LRCF o0 deg

DREF 5G I Rp 1435o040 IN YMRP D oor IN ZMR1 3r70004 IN

MACH 0710 SCALE O0050

PAGE 46

FIGURE 6 CHARACTERISTICS INPITCH- WIDE BODY GRBITER

0

4

4

U

Li e

5J J

3_4 0 10-- a 2 4 8 se 14 le

ANGLE OF ATTACK ALPHA DEGREES DATA =1 SYMBOL CONFIGURATION DESCRIPTIO BETA ELEVNS RUDDER REFERENCE INFORMATION

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BREF 68360 N XMRF 4850040 IN YMRp 0 al I ZHRP 37t00 4 IN

MACH 0900 SCALE DIV050

PAGE 47

4

FIGURE 6 CHARACTERISTICS INPITCH- WIDE BOOY ORBITER

Ar

a t 3 4 IS

ANGLE OF ATTACK ALPHA DEGREES rCRENCC INFORHATIOU

INCR05 a FTT-035 CCNF ROS-W51 82WVZ 0000 0000 0000 SREF 206900 SQIN

CR064) G FTT-055 CCNF RCS- l B2Wl

DATA SET SYMUC C FIGURATIOH DESCRIPTION BETA ELEVNS RUDDER R

0600 U00D LREF 96500 IN

BREF 58380 IN IN14850040XNRP

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SCALE 00050 MACH 1160

PAGE 4B

FIGURE 6 -CHARACTERISTICS INPITCH- WIDE BODY ORBITER

4

3f

U

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oZ 0 EB 0s 10 12 14 16 18 0 _ zz 84

DRAG COEFFICIENT CO DAIA 3ET SY9M CCNFIGURATION DESCRIPtI6 BETA ELEVNS RUDDER REFERENCE INFORMATION RC R 0 5 5 )

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2 WI V a Bawl

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0 0 0 0 SREF 2 O o 6g09 0 0 [ 50

3 IN

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PAGE 49

L4

FIGURE 6 CHARACTERISTICS INPITCH- WIDE BODY ORBITER

IB

Li] 22 o 0 06 6 1 2 1 16 a o 1

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DRAG COEFFICIENT CD DATA SET SYMBOIL CONFIOURATICN DESCRIPTION IRCROS) OFTT-035 COF RO$-WB1 BZWIVZ

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ao00 000a

RUDDER 0000aREF


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PAGE 50

FIGURE 6 CHARACTERISTICS INPITCH- WIDE BODY OBITER

uU

Ishyz 4Ro1 __l_____ ________

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BREF 50300 IN XMRP 14550040 IN YNRP 0OO0t IN Z)4RP 3170004 IN

MACN 11ev SCALE 00050

PAGE 51

--

FIGURE G CHARACTERISTICS INPITCH- WIDE BODY ORBITER rrrr rrl~~ml mrTr r p urr inrmrTr orl I-rJ Jrfmr - rrr T lrr ml im Em m

4

-

Lu

bull 03 025 020 015 010 005 000 - 905 - 01U - 015 - 020 - 02j -2130- 03 - 4l - 045 -050 055

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PAGE 52

FIGURE CHARACIERISTICS INPITCH- WIDE BODY ORBITER -twv- rT Irrsrl~Jrrrr~w r-1 -l J~l rTTT~lD~l l~ -ri-rulw w W~~l1

6

5

4shy

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PITCHING MOMENT COEFFICIENT CLM DATA SET SYM8L CONFIGURATIONDESCRIPTION BETA ELEVN$ RUDDER REFERENCE INFORMATION (RCR 055) 2 GFT-35 CONF ROS-WB1 02WIV2 no DUO 0 0D BREF 20 $SOD 301mo (RCRO) GFTT-035 COF ROS-WO1 S2Wl canO 000O0 LREF 65no IN

BRCF 5830 IN

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W cent 00 SCALE 00050

PAGE 53


-L I

PITCHING MOMENT COEFFICIENT CLM DATA SET SYMBOL CONFIGURATION DESCRIPTION BETA ELEVNS RUDDER REFERENCE INFORMATION CRO55) Q OFTT-03Z CONF ROS-W5 ORWIV2 BD BO B RF 290 $ (CRO14) Ll FTT-OSS COMF R0S-WBI 82WI o 000D LREF 96500 IN

IN58380BREFXHRP 1465d040 INYNRP OUO IN ZMRp 11 04 INSCALE -- o$MACH 1160

PAGE 54

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA=O)g rr rrr m n- I rI r-in r-rrcl-rrrr rrrr rrrv rrrrr-s- rrr rr rr -rl-n-Tmll+--rr -rrrr trw

086

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0

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15

zr

UR

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SIDE SLIP ANGLE BETA DEGREES DATA 4ampT SYMBOL CONFIOURATION DESCRIPTION ALPHA ELEVNS RUDDER (9cRDose W IFT-035 CONF RO$-I 52WIVZ 0000 00D0 00O0 CRCR067) 2 TT-115 COMH 8102-w 8M 0 000 0000

HACH Uo o

9 is is 13 14

REFERENCE INFORMATION SRCF 206900 $41N LREF 96500 IN -RjF 588 IN

-NRP O0W0D IN

SCALE 000S0

PAGE 55

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA=O)

025 - - -- - - - - - - - - - - - - - - -

-I-5

z I - o

z C-G

SIDE SLIP ANGLE BETA DEGREES VATA SET SYMSM CONFIGURATIM DESCRIPTICN ALPHA ELrVNS RUDDER REFERENCE INFORNATION

IRCROG77 OFTT-035 CCF R05-w Bzwi a000 0000 LREF 96500 IN

OREFIHRP

583aO 148504

IN [N

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YMRP ZHRPSCALE

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I IN

PAGE 56

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER [ALPHA=O]

020

77

015

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2-D

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Li-

IDEDSLPAGLBTDGRE

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PAGE 57

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BOY ORBITER [ALPHA=0)

-

to

m to

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-o

z

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-05

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SIDE SLIP ANGLE BETA DEGREES DATA SET SYMBOL CONFIGURATION DESCRIPTION ALPHA ELEVNS RUDDER REFERENCE INFORMATION (RCROSS) OFTI-035 COF Mos WBI 92WIV2 0 0 0 BODO 0000 SREF 2C6900 SeIN

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PAGE 58

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA=O]

05

m

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u

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to

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SIDE SLIP ANGLE BETA DEGREES DATA SET SYMBOL CONFIGURATION DESCRIPTION ALPHA ELEVNS RUDDER REFERENCE INFORMATION I RCAU58) GFTT-035 CONF Ro _WSI 8 IV 0 Do aOno n000 SRpoundF 206o0 5QIN

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SCALE ODJ5 aMACH U9013

PAGE 59

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY IRBIER (ALPHA=0)

000

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SIDE SLIP ANGLE BETA DEGREES DATA SET SYMBOL CONFIGURATION DESCRIPTION ALPHA ELEVN$ RUDDER REFERENCE INFORMATION (R R58)

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IN in

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IN IN

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PAGE 60

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER [ALPU=AO)

I-

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u

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tj~l Li 0

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0 --5

1 2 3 14 s t54 5 7 1-6 -

SIDE SLIP ANGLE BETA DEGREES R FEREN C INFOR ATIO NVNS DDERALPHA L R

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RC 5) FTT-- 55COfiRO Si-WSX VEIlV E LREF 9 6500 IN000 00

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PAGE 61


InI I-I

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4 3 2 1 a 1

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DATA SET SYMOL CFIGURATION DESCRIPTIONIRCRO58) 0 OFTT-035 CONF ROS-WS1 D2WIVZ( R67) Ls FTT-vas CmF Roo-wal DzwI

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9 IV 21 le 13 14

REFERENCE INFORMATION S EF 206900 SQIN LREF 96 0 IN

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PAGE 62

FIGURE 7 CHARACTERISTICS INSIDESLIP- WIDE BODY RBITER (ALPI-A=O)

I-I C-

Lii

Lushy

3 0 4 Ia- - 2 1- 0 3 4 5 6 7 a 9 0 1 1 s 2 13 4

SIDE SLIP ANGLE BETA DEGREES DATA SET SYMOCamp CONFZGRAZI ECI ALPHA ELEVNS RUDDER REFERENCE INFORMATION

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OREF 58a0

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PAGE 63

FIGURE 8 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA= 10]ca I

09 shy- 0

010

M GD5

In

z -

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u

Cshy

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REFERENCE FILE

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ALPHA RUDDER

10000 ODv

CLEMHS 000D $REF LREF

206900 9

SQIN

0 -P 16 REF 583SO014850040 ININ

SIP SLP A E DN ZNRP 37700004 IN

SCALE 00050

GFTT-035 CONF ROS-WBI B2W1V2 (RCRO613 10 AUG 71 PAGE 64

I-3

FIGURE 8 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA= 10)0~ ~ ~~~ rrfrr7 1

S S

on

I- ogg

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SIDE SLIP ANGLE BETA DEGREES SYN6CL MACH PARAMETRIC VALUES RCFEREUCC INFORMATZtQ

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FIGURE 8 CHARACTERISTICS INSIDESLIP- WIDE BODY ORBITER (ALPHA= I0)

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REFERENCE FILE SCALE 0005C

GFTT-035 CONF RCS-WBI B2WIV2 (RCRO61) 10 AUG 71 PAGE GG

--

FIGURE 9 LONGITUDINAL CHARACTERISTICS- NARROW AND WIDE BODY CINFIG ATIONS ~~~ bull o

Ld

Co

n _ 20

u 25

lt

z- 15

u

Ld

00

H

01 09 D D4 05 0G 07 00 Q9 10 12 2 13 S4 15

MACH NUMBER DATA SET SYMBOL CONFIGURATION DESCRIPTION REFERENCE INFORMATION tZCROZI) FTT-U35 COMF ROS-NSI 01WIVI SREF 20SO QZN CZCRO65S R IFTT-0[35 COMIFROS-W]51 S2WJV2 LREF 966SI

DR 588 IN XmRP 1465 GU40 IN YIRP ZMR

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IN1N

SCALE aOS

PAGE 67

FIGURE 9 LONGITUDINAL CHARACTERISTICS- NARROW AN) WIDE BODY CW IGURATIWS hi ui

o - 010

hi

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09

(-3

N

lt oOV S

0 - 050

C-hi

lt -055

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z n o

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fshy

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MACH NUMBER DATA SET 8yVO CONZFIGURATIOI ESCRIPTION REFERENCE INFORHATION IZC0Ozplusmn3 (ZCR055)

Q Ll

GFTT-S5 CONF ROS-ND GFTT-035 CONF RO-hSt

BIWIVI SSWIV

SREF LRIFl

206900 20500

SQplusmn ZN

BREF 58380 IN XNRP 1450 IN tIMRP u0000 IN ZRP 377004 IN SCALE 00050

PAGE 68

FIGURE 9 LONGITUDINAL CHARACTERISTICS- NARROW AND VIDE BODY CONFIGURATIONS

00

z 0

LIshy

0 0

col 05

XS 04

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02

0 01 02 03 04 05 06 0 08 09 10 11 12 13 14 15

MACH NUMBER DATA SET SYMBO CONFIGURATION DESCRIPTION REFERENCE INFORMATION tflcf021) 0 FTT-03S CONV ROS-NSI 8WtVi SACK g0o 0 QIN(0Cft055) LI FTT-035 CONF ROS-Wl B2W3oV2 LREF 90500 ZN

SREF 58900 ZN

XHMP 14050 INYMRP 0001 IN

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PAGE 69

FIGURE 10 LATERAL-DIRECTIONAL CHARACT- NARROW AfND VIE BODY COfWIG (LPHA=O)

car

0 010

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a oLJ002

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MACH NUMBER OATA SET SYISOL CCNFZOURATICN VESCRIpTIC0 REJFERENCE INFORKATION RCRU46) 0 GFTT-055 CCWF ROS-N81 S1Wl SRJEF 20 0 S4i N IRdegR028) L26 GFTT-035 CONF ROS-No Stwiv1 LREF 9deg 5a IN IMCR049) S COMF RWNalrFTT-035 BIWZV3 BREF 58380 IN CR7) MFT--I CM F NOS=k~ B2WJ1 XKRp 14050040 IN (RCRO58) OFTT-035 CCNF R0S-Will BZWV2 YNRP 000- INo

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PAGE 70

FIGURE 10 LATERAL-DIRECTIONAL CHARACT- NARROW AND WIDE BODY CONFIGo (ALPIA=0] II I r 04 I I - I

038

cx 03 0 car

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MACH NUMBER DATA SET SYMBOL CONFIGURATION DESCRIPTION REFERENCE INFORMATION (RCRO4S) (RCR28) CRCRO49S

GFTT-035 CONF ROS-NDI OFTT-035 CONF ROS-NfS GFTT-035 CONF ROS-NO

DM SItVEn BI3WZ

SREF LRCF BREF

206900 96500 58380

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PAGE 71

FIGURE 10 LATERAL-DIRECTIONAL CHARACT- NARiROW AND WIDE B5DY CONFIG (ALPHA=O)

- 007

Lii

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shy- 0185o

DATA SET RCRD46)

IRCRO28)1RD9 (ACRG) cRCRD56)

at0 01 2 03 04

SVMBOL CONFIGURATIOH DESCRIPTION FTT-035 CONF ROS-N8 131I

FT-1U35 CONF ROS-Mi ali Vs

GT-35 CONF RO$-NBI BAV2V3 GFTT-Ds CQN RO-wal Bewi OFTT-035 CONF ROS-IZl 0IV2

05 06 07 06 09

MACH NUMBER

10 X1 1L2 1 1 4 5

REFERENCE INFORMATION SREF 206900 5STN LREF 96500 IN BRIEF 58380 IN XKRF 14850040 IN YwRF 0000 ]IN ZMRP 377 0024 IN SCALE a050

PACE 72

FIGURE I1LATERAL-DIRECTIONAL CHARACT- NARROW AND WIDE BODY CONFIG (ALPHA=IO)

014

0 0 - II--

LLI Ix

(- 004

j 013 -I

u 009

0

z

-- 00

LI

(9) - 02

z

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MACH NUMBER DATA WT OYMSOM CONFIGURATION DESCRIPTION REFERENCE INFORMATION

1RCRD31)1RCROGII

GOFTT-035 CONF ROS-NSI GFTT--035 CONF ROS-WOI

BIWIVI B2WV2

SREF LR[f

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SBIi IN

BREF 5835 IN IRp 1485004d IN YHRp ZNRp

0 00 770004

INO IN

SCALE 00050

PAGE 73

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

FIGURE I1LATERAL-DIRECTIONAL CHARACT- NARROW AND WIDE BODY CONFIG (ALPHAIO)

085

Lii

Lii

018

- os

(0 005 - 010C 0

-o CD

- 005

ashyz- O

Lii - o10

LI

S

5

0 S-0315

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MACH NUMBER DATA SET SYMBOL CONIGURATION DESCRIPTION REFERENCE INFORMATION

RCRD3l ) OFTT-035 CONF ROS-051 BlWlVl SREF 206900 seIa

I CROSS) ampFTT-035 COMF 1R

ROS-W9I 92WIV2 LREF F

96500 5 85 0

1 N IN

Pp 485oO40 IN YRP a Soon IN ZNRpSCALE

3T770004G0050

IN-

PACE 7U

FIGURE 11 LATERAL-DIRECTIONAL CHARACT- NARROW AND WIDE BODY COIfIG CALP = O)E r

- 0140

-0amp44 - 0142 shy

- 9140

Lii

en o-LL -0100 -

V9

C - 0154

ou - 0156

Li - 0156

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rr 13152 LiLu -0164

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O 0166

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00 01 02 03 04 05 amp6 07 0 v9 10 11 12 13 14 15

MACH NUMBER DATA SET SYNOS CONFIGURATION ESCRIPTION REFERENCE INFORNATION (RCRVfl) GFlT-05 COIF ROS-NDl SIWlIy SJREF 9069u0 SQIN (RCROGI) 2 GFTT-035 ConF ROS-wZ SZWIVz LREF 965b IN

BREF 5O8S80 IN Y$RP 14050040 IN

0NRP IN0000


PAGE 75

NASA Series Number S-0607 DM5-DR-11 6 1 AUGUST 1971

SADSACSPACE SHUTTLE

WIND TUNNEL TEST DATA REPORT

CONFIGURATION Grumman Configuration ROS-NB1 and ROS-WB1

TEST PURPOSE Determine basic transonic force data for two delta wing

orbiter configurations (M = 07 - 116)

TEST FACILITY Grumman Farmingdale 26 transonic tunnel

TESTING AGENCY Grumman Aerospace Corporation

TEST NO amp DATE GFTT - 035 31771 to 42171

FACILITY COORDINATOR M Quan GAC

PROJECT ENGINEER(S) F Manke GAC

R Krepski GAC

B Johannesen GAC

DATA MANAGEMENT SERVICES

LIAISON L~_DATA OPERATIONSjoanl Z vaugn a4

RELEASE APPROVAL 1p DbullKemp upervisor

Aero Therme-Wata Group

CONTRACT NAS 8-4o6 AMENDMENT 153 DRL 184 - 58

This report has been prepared by Chrysler Corporation Space Division under a Data Management Contract to the NASA Chrysler assumes no responsibility for the data presented herein other than its display characteristics



Phone (516) 575-7o44

PROJECT ENGINEERS


Phone (516) 575-7044 Phone (516) 575-7044


Phone (516) 575-7044



Phone (205) 895-1560 Phone (504) 255-2304

ABSTRACT














TABLE OF CONTENTS

PAGE NUMBER


SUMMARY 3




TEST CONDITIONS 7

DATA REDUCTION 8


FIGURES 12




PLOTTED DATA 34

1~

LIST OF FIGURES


1 Axis System 13




5 W2 - Wing 17


LIST OF TABLES



2

SUMMARY










Ems-DR-1081 017

DmS-DR-1161 07 to 115


DMS-DR-1159 100




of attack

3















4









RCP-0o4 _jQ 8 B 00 shy 3 44 47 -5


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CcaOG7~J 05 B367 0 49 69

1 7 3 19 25 31 - 37 943 55 61 67 7576








section


Mach Range o6 to 13









6



deg 7 73 x 1O6 620 30

1068 79 x 741- 30 308299 83 x 1o6

bull 86 x lo6 868 300

300996115 87 x lo6


COEFFICIENT


AF 80 1b 7L2T 0 PM 300 _-357In-ib 0003

M 125 in-ib -192A 0013 207 0003R4 80 in-lb

COMMENTS

7

DATA REDUCTION











8


SADSAC NOMENCLATUI

COEFFICIENT

CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME



Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment





BODY AXIS

CA CAB CAF

---

-

CN

CY

CBL

CLM

CYN

NA

CNCAF


-shy

- -


CL CL

- -

CY CC

CSL CWL

CLM CPM

CLN CLN

LD CLCD

LDF CLCDF

- -

- -


PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


-3 - 13


0

PAGES

1-5


- B Configuration 07-116 -3 - 13 0 6-15


--


07-116 -3 - 13 0 16-18



07-116 -3 - 13 0 19-24



07-116 -3 - 13 0 25-33



D Configuration 07-116 0 -4 - 12 34-42




A Configuration 07-116 -4 - 12 0 46-48


- B Configuration 07-116 -4 -- 12 0 49-54




PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



CL vs a CL CL

vs vs

CD CIM

CUN CSL CY

vs vs vs

a a a


cIN CSL c

vs vs vs

P P P


CD(MIN) vs


d(CN) d(CSL)

d(C)

vs vs vs


FIGURES

12




IZ

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CLL


NA$A-MSFC-AAF

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z



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0

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(X2oo SCALE)

H 425

-



19






Length i608 9648

Max Width 280 168o

Max Depth 287 1722

Fineness Ratio 3 61

Area


Planform 990 14364

Wetted i 6-y 45396

Base 59r 2124

20





MODa ScALE


(INOR IN 2 ) 9648

Max Width 448 -2fa

Max Depth 288 17PR


Area


Planform 516o

Wetted f2 47-628

Base 7- 2678

21








-129 0o0

odY -3 tip

IP9




T2-90 Z2a U


i046 135

6P76 81o



EXPOSED DATA

Area 3217 11-81



22




DIMENSIONS

Area


364


110


1chord 1275 T65



At Inbd equiv chord




Tailing Edge 8

Hingeline


23






Area 805 2898










Hingeline 2870 287



24

NASA-MSFC-MAF



Vertical Tail




Area 240 864


chord 104 624








Hingelne





DIMENSIONS

Area

Span (equivalent)




At Inbd equiv chord



Leading Edge

Tailing Edge

Hingeline


AIRFOIL SECTION



2rop

1990

534

400

85deg

NAA 64A010

150

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670

5521

3317

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400

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26




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Area CPT oR I)

684 (INcen TN) 2462














27

NCMENCLA

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28



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S

S

SYMBOL

SREF

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wing area m2 ft2




bref

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2g


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SYMBOL DEFINITION

F force F lbs

M moment M in-lb


N normal force

A axial force

L lift force

D drag force





w wind axissystem



t total conditions

b base

30

SADSAC SD4OL SYI4BL

CL CL

CD CD

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CDf OF

Cm CTm

CY

Ch CIN

C CSL

LD LD

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31


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0

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DEFlTION




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32

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Phone (516) 575-7o44

PROJECT ENGINEERS


Phone (516) 575-7044 Phone (516) 575-7044


Phone (516) 575-7044



Phone (205) 895-1560 Phone (504) 255-2304

ABSTRACT














TABLE OF CONTENTS

PAGE NUMBER


SUMMARY 3




TEST CONDITIONS 7

DATA REDUCTION 8


FIGURES 12




PLOTTED DATA 34

1~

LIST OF FIGURES


1 Axis System 13




5 W2 - Wing 17


LIST OF TABLES



2

SUMMARY










Ems-DR-1081 017

DmS-DR-1161 07 to 115


DMS-DR-1159 100




of attack

3















4









RCP-0o4 _jQ 8 B 00 shy 3 44 47 -5


gc05g B2W Vplusmn o 5 0 0 0 3 58 3 - _


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section


Mach Range o6 to 13









6



deg 7 73 x 1O6 620 30

1068 79 x 741- 30 308299 83 x 1o6

bull 86 x lo6 868 300

300996115 87 x lo6


COEFFICIENT


AF 80 1b 7L2T 0 PM 300 _-357In-ib 0003

M 125 in-ib -192A 0013 207 0003R4 80 in-lb

COMMENTS

7

DATA REDUCTION











8


SADSAC NOMENCLATUI

COEFFICIENT

CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME



Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment





BODY AXIS

CA CAB CAF

---

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CN

CY

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CLM

CYN

NA

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CSL CWL

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PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


-3 - 13


0

PAGES

1-5


- B Configuration 07-116 -3 - 13 0 6-15


--


07-116 -3 - 13 0 16-18



07-116 -3 - 13 0 19-24



07-116 -3 - 13 0 25-33



D Configuration 07-116 0 -4 - 12 34-42




A Configuration 07-116 -4 - 12 0 46-48


- B Configuration 07-116 -4 -- 12 0 49-54




PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



CL vs a CL CL

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12




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Area


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Wetted i 6-y 45396

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EXPOSED DATA

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23






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Hingeline 2870 287



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DIMENSIONS

Area

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SYMBOL DEFINITION

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M moment M in-lb


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A axial force

L lift force

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t total conditions

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30

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31


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ABSTRACT














TABLE OF CONTENTS

PAGE NUMBER


SUMMARY 3




TEST CONDITIONS 7

DATA REDUCTION 8


FIGURES 12




PLOTTED DATA 34

1~

LIST OF FIGURES


1 Axis System 13




5 W2 - Wing 17


LIST OF TABLES



2

SUMMARY










Ems-DR-1081 017

DmS-DR-1161 07 to 115


DMS-DR-1159 100




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3















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section


Mach Range o6 to 13









6



deg 7 73 x 1O6 620 30

1068 79 x 741- 30 308299 83 x 1o6

bull 86 x lo6 868 300

300996115 87 x lo6


COEFFICIENT


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COMMENTS

7

DATA REDUCTION











8


SADSAC NOMENCLATUI

COEFFICIENT

CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME



Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment





BODY AXIS

CA CAB CAF

---

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CN

CY

CBL

CLM

CYN

NA

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CL CL

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CY CC

CSL CWL

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CLN CLN

LD CLCD

LDF CLCDF

- -

- -


PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


-3 - 13


0

PAGES

1-5


- B Configuration 07-116 -3 - 13 0 6-15


--


07-116 -3 - 13 0 16-18



07-116 -3 - 13 0 19-24



07-116 -3 - 13 0 25-33



D Configuration 07-116 0 -4 - 12 34-42




A Configuration 07-116 -4 - 12 0 46-48


- B Configuration 07-116 -4 -- 12 0 49-54




PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



CL vs a CL CL

vs vs

CD CIM

CUN CSL CY

vs vs vs

a a a


cIN CSL c

vs vs vs

P P P


CD(MIN) vs


d(CN) d(CSL)

d(C)

vs vs vs


FIGURES

12




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Length i608 9648

Max Width 280 168o

Max Depth 287 1722

Fineness Ratio 3 61

Area


Planform 990 14364

Wetted i 6-y 45396

Base 59r 2124

20





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(INOR IN 2 ) 9648

Max Width 448 -2fa

Max Depth 288 17PR


Area


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TABLE OF CONTENTS

PAGE NUMBER


SUMMARY 3




TEST CONDITIONS 7

DATA REDUCTION 8


FIGURES 12




PLOTTED DATA 34

1~

LIST OF FIGURES


1 Axis System 13




5 W2 - Wing 17


LIST OF TABLES



2

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CA CAB CAF

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SCHEDULE

A

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Configuration

NOMINAL MACH

NUMBER

07-116


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0

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D Mach Number 07-116 10 -2 - l 64-66




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DIMENSIONS

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AIRFOIL SECTION



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1990

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Axis System General

SYMBOL DEFINITION

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M moment M in-lb


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LIST OF FIGURES


1 Axis System 13




5 W2 - Wing 17


LIST OF TABLES



2

SUMMARY










Ems-DR-1081 017

DmS-DR-1161 07 to 115


DMS-DR-1159 100




of attack

3















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6



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COEFFICIENT


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COMMENTS

7

DATA REDUCTION











8


SADSAC NOMENCLATUI

COEFFICIENT

CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME



Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment





BODY AXIS

CA CAB CAF

---

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CN

CY

CBL

CLM

CYN

NA

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CL CL

- -

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CSL CWL

CLM CPM

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LD CLCD

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- -

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PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


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0

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1-5


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--


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07-116 -3 - 13 0 25-33



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A Configuration 07-116 -4 - 12 0 46-48


- B Configuration 07-116 -4 -- 12 0 49-54




PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



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Length i608 9648

Max Width 280 168o

Max Depth 287 1722

Fineness Ratio 3 61

Area


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Wetted i 6-y 45396

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20





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21








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22




DIMENSIONS

Area


364


110


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Tailing Edge 8

Hingeline


23






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24

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Hingelne





DIMENSIONS

Area

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Leading Edge

Tailing Edge

Hingeline


AIRFOIL SECTION



2rop

1990

534

400

85deg

NAA 64A010

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670

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27

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SADSAC

SYMBOL

S

S

SYMBOL

SREF

DEFINITION

wing area m2 ft2




bref

Ab


base area 2 ft2 in2






2g


Axis System General

SYMBOL DEFINITION

F force F lbs

M moment M in-lb


N normal force

A axial force

L lift force

D drag force





w wind axissystem



t total conditions

b base

30

SADSAC SD4OL SYI4BL

CL CL

CD CD

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CDf OF

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CY

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C CSL

LD LD

LDf LDF



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31


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c

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f

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Ems-DR-1081 017

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7

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SADSAC NOMENCLATUI

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CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

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LD

L1

NA

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COEFFICIENT NAME



Lift Force

Normal Force

Side Force

Rolling Moment

Pitching Moment

Yawing Moment





BODY AXIS

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---

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CN

CY

CBL

CLM

CYN

NA

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CL CL

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CSL CWL

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LD CLCD

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PLOT TITLE


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SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


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0

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NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



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Max Depth 287 1722

Fineness Ratio 3 61

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Wetted i 6-y 45396

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22




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Hingeline 2870 287



24

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chord 104 624








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Area

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Leading Edge

Tailing Edge

Hingeline


AIRFOIL SECTION



2rop

1990

534

400

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S

SYMBOL

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SYMBOL DEFINITION

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M moment M in-lb


N normal force

A axial force

L lift force

D drag force





w wind axissystem



t total conditions

b base

30

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CD CD

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CY

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31


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SADSAC NOMENCLATUI

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CA CAB CAF

CD CDB CDF

CL

CN

Cy

C1

Cm

C

LD

L1

NA

NA

COEFFICIENT NAME



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Normal Force

Side Force

Rolling Moment

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---

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PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


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0

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1-5


- B Configuration 07-116 -3 - 13 0 6-15


--


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07-116 -3 - 13 0 25-33



D Configuration 07-116 0 -4 - 12 34-42




A Configuration 07-116 -4 - 12 0 46-48


- B Configuration 07-116 -4 -- 12 0 49-54




PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



CL vs a CL CL

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CUN CSL CY

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a a a


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Max Depth 287 1722

Fineness Ratio 3 61

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20





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534

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w wind axissystem



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30

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31


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PLOT TITLE


-


SCHEDULE

A

CONDITIONS VARYING

Configuration

NOMINAL MACH

NUMBER

07-116


-3 - 13


0

PAGES

1-5


- B Configuration 07-116 -3 - 13 0 6-15


--


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PLOT TITLE



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NUMBER




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PLOT TITLE



NOMINAL MACH

NUMBER




D Mach Number 07-116 10 -2 - l 64-66




F Configuration 07-116 0 -5 - 5 70-72


F Configuration 07-116 10 -5 - 5 73-75



CL vs a CL CL

vs vs

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Fineness Ratio 3 61

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23






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SYMBOL DEFINITION

F force F lbs

M moment M in-lb


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L lift force

D drag force





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t total conditions

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30

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31


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