NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

NASA CR-

/a. yyigjL

{NAS~A-GR- 134433) SUBSONIC AND TRANSONIC ' N75-13824

BINGE MOMENT AND WING BENDING/TORSION CHARACTERISTICS OF’ .015 SCALE SPACE

' SHUTTLE. MODELS 49.-0 AND 67-TS IN THE . Unclas

t (Chrysler Corp.) •, 1096 p HC $25.25 G3/02 06512 J

SPACE SHUTTLE

AEROTHERMODYNAMIC DATA REPORT

JOHNSON SPACE CENTER iEdNagement services

HOUSTON, TEXAS

SPACE DIVISION

CHRYSLER

CORPORATION

.-■DATE : Jar>uary 1975

THE FOLLOWING CHANGES APPLY TO PUBLICATION :DMS Data Report

TITLE: SUBSONIC AND TRANSONIC HINGE MOMENT AND WING BENDING/TORSION

CHARACTERISTICS OF .015 SCALE SPACE SHUTTLE MODELS 49-0 AND 67-TS IN THE

ROCKWELL INTERNATIONAL TRISQNIC WIND TUNNEL (IA701

Vol . 3 * —

NUMBER: DMS-DR-2175 DATE: NOVEMBER 1974 BRANCH:FLIGHT TECHNOLOGY

CONTRACT: NASA Contract No, NAS9-13247

Correct DMS-DR-2075 to DMS-DR-2175 on title page.

Prepared by: Liaison— D. A. Sarver, M. J. Lanfranco

Operations— D. E. Poacher

Reviewed by: „G1ynn

Approved:

K'emp, Manager Data Management Services

Concurrence:

J yG. Swi der , Manager Flight Technology Branch

PAGE l OF l

DISTRIBUTION SAME AS FOR ABOVE PUBLICATION

D<f2T^3 <ffl^f\jagemerrt services

SPACE DIVISION

CHRYSLER

CORPORATION

November, 1974

DMS-DR-2175 NASA CR- 134,433

VOLUME 3 OF 3

SUBSONIC AND TRANSONIC HINGE MOMENT AND

WING BENDING/TORSION CHARACTERISTICS OF .015' SCALE SPACE SHUTTLE MODELS 49-0 AND 67-TS IN THE ROCKWELL INTERNATIONAL TRISONIC WIND TUNNEL (IA70)

By

M. T. Hughes and R. C. Mennell Shuttle Aero Sciences Rockwell International Space Division

Prepared under NASA Contract Number NAS9-13247

By

Data Management Services Chrysler Corporation Space Division New Orleans, La. 70189

for

Engineering Analysis Division Johnson Space Center

National Aeronautics and Space Administration Houston, Texas

WIND TUNNEL TEST SPECIFICS:

Test Number:

NASA Series Number: Model' Numbers:

Test ■ Dates : Occupancy Hours:

Rockwell Trisonic - 282 IA70

49-0, 67-TS 3 through 24 May 1974 161

FACILITY COORDINATOR: •

R. B. Russell

Rockwell International .B-l Division Mail Stop BD02

Los Angeles International Airport Los Angeles, California 90009

Phone: (,21.3) 670-9151 x3343

PROJECT ENGINEERS:

AERODYNAMICS ANALYSIS ENGINEER:

M. T. Hughes,

R. C. Mennell Rockwell International B-l Division Mail Stop BD02

Los Angeles international Airport Los Angeles, California 90009

Phone: (213.) 670-9151 x'3343

C. F. Ehrlich, Jr. Rockwell International Space Division 12214 Lakewood Blvd.

Mail Stop AC07 Downey, California 90241

Phone: (213) .922-5060

DATA MANAGEMENT SERVICES:

Prepared by: Liaison— D. A. Sarver, M. J. Lanfranco

Operations — D. E. Voucher

Reviewed by: J. L. Glynn

Approved: 0.

Kemp

D. KM, Manager lata Management Services

Concurrence:

/=£/e J. G. Swiderj Manager

Fliaht Technology Branch

Chrysler Corporation Space Division assumes no responsibility for the data presented other than display characteristics.

n

SUBSONIC AND TRANSONIC HINGE MOMENT AND WING BENDING/TORSION CHARACTERISTICS OF .0.15 SCALE SPACE SHUTTLE MODELS 49-0 AND 67-TS IN THE ROCKWELL INTERNATIONAL TRISONIC WIND TUNNEL (IA70)

By

M. T. Hughes and R. C. Mennell Rockwell International Space Division

ABSTRACT

Experimental aerodynamic investigations were conducted on an 0.015- scale representation of the VL70-000140A/B Integrated Space Shuttle Launch Vehicle in the Rockwell -International Trisonic Wind Tunnel from 3 May 1974 to 24 May 1974. The primary test objective was to obtain subsonic and transonic elevon and bodyflap hinge moments and wing bending-torsion mo- ments in the presence of the launch vehicle. Wing pressures (42) were also recorded for the upper and lower right wing surfaces at two spanwise stations (n = 0.436 and 0.771).

The hinge moment, wing bending/torsion moments and wing pressure data were recorded over an angle-of-attack («) range from -8° to +8°, an angle- of-sideslip (8) range from -8° to +8° and at Mach numbers of 0.90, 1.12, 1.24 and 1.50. The Reynolds number for all Mach numbers was approximately 7.0 x 106/foot.

Outboard elevon deflections of 0°, ±4° and ±8°; inboard elevon de- flections of 0°, +4°, +8° and +12°; and bodyflap deflections of 0° and

+10° were tested over the entire Mach number range.

Tests, were also conducted to determine the effects of the Orbiter rear attach cross, beam and the forward attach wedge and strut diameter. The Orbiter alone was tested at 0.90 and 1.24 Mach number only.

For both the Orbiter alone and integrated configurations the models were sting ‘mounted on a dummy 1.5-inch Task MK XXVII balance pinned in the Orbiter.

This report consists of three volumes arranged in the following manner:

Volume 1 - Plotted and tabulated force data

- Plotted pressure data - Figures 25 and 26

Volume. 2 - Plotted pressure data - Figures 27 through 32

Volume 3 - Tabulated pressure data

TV

TABLE OF CONTENTS

Page

ABSTRACT i i i

INDEX OF MODEL FIGURES 2

INDEX OF DATA FIGURES 3

NOMENCLATURE j

CONFIGURATIONS INVESTIGATED H

TEST FACILITY DESCRIPTION 15

DATA REDUCTION 17

TABLES

I. TEST CONDITIONS 21

II. DATASET/RUN NUMBER COLLATION SUMMARY 22

III- MODEL DIMENSIONAL DATA 26

IV. PRESSURE INSTRUMENTATION 53

FIGURES

MODEL 54

APPENDIX

TABULATED PRESSURE DATA 67

INDEX OF MODEL FIGURES

Figure	Title	Page
T.		Axis systems.
	a.	General	54
	b.	Model Attitude Definition	55
	c.	Sign Convention for Control Surfaces	56
2.		Model sketches.
	a .	General Arrangement, -140A/B Orbiter	57
	b.	Mated Vehicle Configuration	58
	c.	Forward Orbiter/ET Attach Hardware	59
	d.	Aft Orbiter/ET Attach Hardware	60
	e.	Elevon and Body Flap Hinge Moment Gage i Wing Bending and Torsion Gage j	61
	f. ’	62
	g.	Installation Sketch	63
	h.	Orbiter Wing Pressure Tap Locations	•64
3.		Model installation photographs.
	a.	Aft View, TWT Installation Orbiter B2g Cg M7 F7 W^g e? v8 r15	65
	■b.	Aft View, TWT Installation Orbiter + External Tank + Solid Rocket Motors	65
	c.	Front View, TWT Installation Orbiter + External Tank + Solid Rocket .Motors	66

2

INDEX OF DATA FIGURES

SCHEDULE OF

FIGURE				COEFFICIENTS	CONDITIONS
NUMBER	TITLE .		-	PLOTTED	VARYING	PAGES
VOLUME
Fig. 4	Longitudinal Buildup,	Elevon = 0	(A)	MACH	1-12
Fig. 5	Elevon Effectiveness,	Otbd	Elevon - 0	(B)	MACH ELV-LI ALPHA	13-32
Fig. 6	Elevon Effectiveness,	Otbd	Elevon -= 4	(B)	MACH , • ELV-LI	33-52
	'	"			ALPHA
Fig. 7	Repeatability			(A)		53-55
Fig. 8	Elevon Effectiveness,	Otbd	Elevon = 8	(B)	MACH ELV-LI ALPHA	56-73
Fig. 9	Elevon Effectiveness,	Otbd	Elevon - -4	(B)	ELV-LI ALPHA	74-78
Fig. 10	Elevon Effectiveness,	Otbd	Elevon = -8	(A)	ELV-LI	79-81
Fig. 11	Elevon Effectiveness,	Inbd	Elevon = 0	(C)	MACH ELV-LO ALPHA	82-101
Fig; 12	Elevon Effecti veness ,	Inbd	Elevon = 4	(C)	• MACH	102-121

ELV-LO

ALPHA

		INDEX OF DATA FIGURES	(Continued)
FIGURE		SCHEDULE OF COEFFICIENTS	CONDITIONS
NUMBER	TITLE	PLOTTED	VARYING	’ PAGES
Fig.	13	Elevon Effectiveness, Inbd Elevon = 8	(C)	MACH ELV-LO Alpha	1 22-141
Fig.	14	Elevon Effectiveness, Inbd Elevon = 12	(C)	MACH ELV-LO ALPHA	142-161
Fig.	15	Effect of Yaw, DEO - -4, DEI = 8	(A)	BETA	162-164
Fig.	16	Effect of Yaw, DEO = 0, DEI = 12	(A)	BETA	165-167
Fig.	17	Effect of Yaw, DEO = 4, DEI = 12	(A)	BETA MACH	168-173
Fig.	18	Effect of Yaw, DEO = 4, DEI * 4	(A)	BETA	174-176
Fig.	19	Effect of Yaw, DEO = 8, DEI = 8	(A)	BETA	177-179
Fig.	20	Effect of Yaw, DEO = 0, DEI = 0	(A)	BETA	180-182
Fig.	21	Effect of Rear Attach Point Crossbeam, Elevon = 0	(A)	CONFIG.	183-185
Fig.	22	Effect of Foreword Attach Point Configuration, Elevon = 0	(A)	CONFIG.	186-188
Fig.	23	Effect of Yaw on Foreward Attach Point Configuration, Elevon = 0	(A)	BETA	189-191
Fig.	24	Body Flap Effectiveness, Elevon » 0	(D)	8 FLAP ALPHA	192-196

INDEX OF DATA FIGURES (Continued)

FIGURE NUMBER	TITLE	SCHEDULE OF COEFFICIENTS ■ PLOTTED	CONDITIONS VARYING	PAGES
Fig. 25	Wing Pressure Distribution Due' to Elevon Deflection, Beta = 8	(E)	ELEVON MACH ALPHA 2Y/B	197-412
Fig. 26	Wing Pressure Distribution Due to Elevon Deflection, Beta = 4	(E)	ELEVON MACH ALPHA 2Y/B	413-628
VOLUME	_2
Fig. 27	Wing Pressure Distribution, Due to Elevon Deflection, Beta = 0	' (E)	ELEVON MACH ALPHA 2Y/B	629-844
Fig. 28	Wing Pressure Distribution Due to Elevon Deflection, Beta = -4	(E)	ELEVON MACH ALPHA 2Y/B	845-1060
Fig. 29	Wing Pressure Distribution Due to Elevon Deflection, Beta = -8	(E)	ELEVON	1061-1276
Fig. 30	Effect of For'eward Attach Point Wedge, 8 Degree Elevon Deflection 1	(E)	CONFIG. MACH ALPHA 2Y/B	1277-1330
Fig. 31	Effect of Foreward Attach Point Wedge, 0 Degree Elevon Deflection	(E)	CONFIG. MACH ALPHA ' 2Y/B	1331-1384

INDEX OF DATA FIGURES (Concluded)

FIGURE NUMBER	TITLE	SCHEDULE OF COEFFICIENTS PLOTTED	CONDITIONS VARYING	PAGES
Fig. 32	Effect of Rear Attach Cross Beam, 0 Degree Elevon Deflect] pn	(E)	CONFIG. . MACH - ALPHA 2Y/B	1385-1438

1DULE	OF COEFFICIENTS PLOTTED:
(A)	CHEO, CHEI , CHBF, CBW, CTW versus	ALPHA
(B)	CHEO, CHEI, CHBF, CBW, CTW versus CHEO, CHEI versus ELV-LI	ALPHA
(C)	CHEO, CHEI, CHBF, CBW, CTW versus CHEO, CHEI versus ELV-LO	ALPHA
(D)	CHEO CHEI, CHBF, CBW, CTW versus , CHBF versus BFLAP	ALPHA
(E)	CP, DCP versus X/C

NOMENCLATURE

General

SYMBOL	PLOT SYMBOL	DEFINITION
a		speed of sound; m/sec, ft/sec
Cp	CP	pressure coefficient; (p^ - pco)/q
M	MACH	Mach number; V/a
P		pressure; N/m2, psf
q	Q(NSM) q(psf)	dynamic pressure; l/2 pV2, N/m2, psf
rn/l	rn/l	unit Reynolds number; per m, per ft
V		velocity; m/sec, ft/sec
a	ALPHA	angle' of attack, degrees
0	BETA	angle of sideslip, degrees
	PSI	angle of yaw, degrees
	PHI	angle of roll, degrees
P		mass density; kg/m^, slugs/ft^
		Reference & C.G. Definitions
Ab .		base area; m2, ft2
b	BREF	wing span or reference span; m, ft
c.g.		center of gravity
-^REF c	LREF	reference length or wing mean aerodynamic chord; m, ft
S	SREF	wing area or reference area; m , ft‘
	MRP	moment reference point
	XMRP	moment reference point on X axis
	YMRP	moment reference point on Y axis
	ZMRP	moment reference point on Z axis

SUBSCRIPTS

b

1

s

t

CO

base

local

static conditions total conditions free stream

7

NOMENCLATURE (Continued) Additions to Standard Listing

Plot

Symbol	Symbol	Description
am		distance from m-| to gage, in
BW		wing panel bending moment, in-lbs
CBF		bodyflap reference chord, in
Ce	•	elevon reference chord, in
°Bw	CBW	wing bending moment coefficient
Chel,	CHEI	inboard elevon hinge moment coefficient
C, he0;	GHEO	outboard eljevon hinge moment .coefficient
C^eT	CHET	total elevon hinge moment coefficient
ChBF	CHBF	bodyflap hinge moment coefficient
gt ‘w	CTW	wing torsion moment coefficient
CP	CP	local pressure coefficient
Op kle	CPLE	wing leading edge pressure coefficient
£p hwl	CPWL	wing lower surface pressure coefficient
Cp rwu	CPWU	wing upper surface pressure coefficient
Gp T	DCP	total (differential) wing pressure coefficient, (upper - lower).
df		distance from, mg to exposed wing root chord, in

8

NOMENCLATURE ( Conti nued) Additions to Standard Listing

distance from to torsion reference center, in body flap hinge moment, in- 1b inboard elevon hinge moment, in-lb

outboard elevon hinge moment, in-lb

wing bending gage moment at station i, in-lb wing panel normal force, lbs wing leading edge pressure, psi

wing lower surface pressure, psi

wing upper surface pressure, psi

O

bodyflap reference area, ft elevon reference area, ft wing panel torsion moment, in-lb

x/c	X/C
2Y/b,n	2Y/B
6 6 , e0L, 61	ELV-1 ELV-LO
6 ,6e2	ELV-2
eIL	ELV-LI
6 ,<Se3	ELV-3
eIR	ELV-RI

chord wise location, fraction of local chord spanwise location, fraction of wing span lefthand outboard elevon deflection angle, deg

lefthand inboard elevon deflection angle, deg

righthand inboard elevon deflection angle, deg

9

NOMENCLATURE (Concluded) Additions to Standard Listing

e0R e4	ELV-4 .ELV-RO	righthand outboard elevon deflection angle,	deg.
6el	DEI	inboard elevon deflection angle, average of and right inboard panels, deg	left
6e0	DEO	outboard elevon deflection angle, average of left and right outboard panels, deg
6BF	BFLAP	bodyflap- deflection angle', deg

10

CONFIGURATIONS INVESTIGATED

The model used for this test period was an 0.015-scale representation of the Rockwell International VL70-000140A/B Space Shuttle Orbiter and Integrated Launch Vehicle. The Orbiter model 'was of the blended wing-body design with double delta wing planfrom (75°/45°ALE), full span split elevons with unswept hingeline, centerline vertical tail, with rudder/speed- brake capability, fuselage canopy and orbital manuevering system (OMS pods), mounted on the aft fuselage sidewalls. The elevon panels were segmented into inboard and outboard panels at Yq = 312.50. Each panel was capable of independent deflection. Both of the left hand elevon panels and the body- flap were instrumented with hinge moment beams. The right hand wing panel was instrumented with two wing bending gages and a wing torsion gage.

The right hand wing panel was also instrumented with 42 upper and lower wing surface pressures at two spanwise locations. The inboard sta- tion was at Yq = 204 (n = 0.436) and had 25 pressures while the outboard was at 361 (n=Q.771) and had 17 pressures.

The external tank (ET), solid rocket boosters (SRB), attach hardware, ventlines and simulated fairings were constructed of aluminum and 17-4 steel. No pressures or forces were recorded on these components.

The forward attach fairing or wedge was removable as was the rear at- tach crossbeam. The forward wedge covered a 33.3-inch diameter strut which attached the Orbiter to the ET. A later strut configuration which was tested was only 11.3 inches in diameter.

CONFIGURATIONS INVESTIGATED (Continued)

The following letter/number designations were used to describe the Orbiter and' integrated launch vehicle configurations:

Symbol Definition

01 Orbiter, B26 Cg M? F? W116 E37 Vg Rg

T-|2 External tank (ET)

S1 Solid Rocket- boosters (SRB) , S-j2 N^

P2 SRB fairings, PS-j , PS2 and PSg

P0 ET Components and Fairings - PT7, PT9, PT, , AT0, AT7?, AT,-,

8 ATU AT27, FLr FL2,.and FR6 1 2 3 9 13

Pq Same as Pg except the rear attach crossbeam

(FRg) is removed

P,n Same as Pft except the forward attach wedge (AT27) fairing is

removed exposing the attach strut ( AT -j 5 ) and FRg is installed

p,. Same as Pg except the diameter of the forward attach strut

.(AT-jg) isyreduced to 0.170 inches (model scale)

The following letter/number designations describe the individual con- figuration components:

Symbol

ATq Attach structure-rear SRB/ET per Rockwell Lines VL72-000106,

y Model dwg. SS-A01168

AT19 Attach structure-left rear ORB/ET per Rockwell Lines VL78-

000050, Model dwg. SS-A01167

AT-,- Attach structure-right rear ORB/ET per Rockwell Lines VL78-

000050, Model dwg. SS-A01167

ATm Attach structure-front SRB/ET per Rockwell Lines VL77-000051A,

Model dwg. SS-A01168

12

CONFIGURATIONS INVESTIGATED . (Continued)

AT-j r Attach structure-front ORB/ET per Model drawing SS-A01 166-4,

33.3 inch diameter

AT 27 Attach structure-front ORB/ET per Model dwg. 5S-A001 255 ,

includes AT15 plus wedge fairing

Orbiter fuselage per Rockwell Lines VL70-000140A/B, Model 110 dwg. SS-A0O147

Cq Obiter canopy per Rockwell Lines VL70-000140A/B, Model dwg.

y SS-A00147

Eo? Orbiter full span, unswept hingeline, Gr unman gapped elevons

per Rockwell Lines VL70-000200, Model dwg. SS-A01256, $S- A00148

F7 Orbiter body flap per Rockwell Lines VL70-000200, Model dwg.

' SS-A01256, SS-A00147

FL-, ET/ORB. LOX feedline per Rockwell Lines VL78-000050, Model

dwg. SS-A01 167

FLn ET/ORB. LH~ feedline per Rockwell Lines VL78-GQGQ5Q, Model

dwg. SS-A0T167

FRfi ET/ORB rear attach structure cross member per Rockwell Lines

VL78-000062B, Model drawing SS-A01256

M7 Orbiter OMS/RCS pods per Rockwell Lines VL70-000145 Model dwg.

' SS-A00147

Non Orbiter OMS engine nozzles per Rockwell Lines VL70-000145,

Model dwg. SS-A00147

Nrt i SRB engine nozzles per Rockwell Lines VL77-000036A, Model dwg.

SS-A01T68

PS1 SRB electrical tunnel fairing per Rockwell Lines VL77-000036A,

s Model dwg. SS-A01168

PSo SRB attach ring per Rockwell Lines VL77-000036A, Model dwg.

SS-A01 168

PSo SRB separation rocket fairing per Rockwell Lines VL77-000036A,

Model dwg. SS-A01168

13

CONFIGURATIONS INVESTIGATED [Concluded)

ET,9 LOX ventline fairing per Rockwell Lines VL78-000031A, Model dwg. SS-A01167,

ET19 LOX feedline per Rockwell Lines VL78-000031A, Model dwg, SS-A01 1

ET19 LH9 feedline per Rockwell Lines VL78-000031A, Model dw^7 SS-A01167

Orbiter rudder per Rockwell Lines VL70-000146A, Model dwg. SS-A00115

SRB per Rockwell Lines VL77-000036A, Model dwg. SS-A01 167

ET per Rockwell Lines VL78-000041B, Model dwg. SS-A01167

Orbiter centerline vertical tail per Rockwell Lines VL70- 0001 46A, Model dwg. SS-A00148

Orbiter double delta wing per Rockwell Lines VL70-000200, Model dwg. SS-A00148

TEST FACILITY DESCRIPTION

The Rockwell International Trisonic Wind-Tunnel is an intermittent blow down facility with a 7’ x 7' tandem test section capable of testing force, duct, pressure, and flutter models at Mach numbers from 0.1 to 3.5.

Two synchronous motor-driven centrifugal compressors, operating in series-, supply dry air at a .rate of 40 lb/sec. to eight storage spheres having a total volume of 214,000 cu. feet. The air is dried to a moisture content of .0001 lb. or less of water per lb. of dry air (approx. .-35°F dew-point) and stored at a pressure of ten atmospheres. Flow from the air storage spheres is regulated by a servo controlled valve. The eight foot diameter valve opens within, two seconds to control and stabilize the .settling chamber at a preselected pressure.

Downstream of the settling chamber is a fixed nozzle which provides a transition from the circular cross-section of the settling chamber to the rectangular cross-section of the variable nozzle. Two seven foot wide steel plates, supported between parallel walls by hydraulic jacks, form the floor and ceiling of the flexible nozzle section. Changes in nozzle con- tours to produce variations in Mach number are accomplished by means of these jacks and require 30 to 40 minutes to complete.

Two test sections, for supersonic, transonic, and subsonic testing are 7 ft. wide by 7 ft. high and are permanently installed in a tandem arrangement. The standard supersonic test section {for testing at Mach numbers greater than 1.3) is in the downstream end of the flexible nozzle'. The test section for subsonic and transonic operation is located downstream

15

TEST FACILITY DESCRIPTION (Concluded)

in the porous wall area. An access door to the test area is located in the variable diffuser.'

The variable diffuser downstream of the porous wall area may be ad- justed to provide subsonic Mach number control, to generate transonic Mach numbers, and to minimize start time for supersonic testing with models having high tunnel blockage;

An equivalent 5° conical expansion angle is' provided in a. fixed dif- fuser which completes the basic- tunnel circuit. Downstream of the diffuser is a sound abatement muffler building where the air is exhausted to the atmosphere.

16-

DATA REDUCTION

The elevon panel hinge moments, bodyflap hinge moments and wing .bend- ing/torsion moments were measured by individual strain gage beams.

The data reduction procedures are as follows:

(1) Compute inboard elevon hinge moment coefficient

^el

chei " '"qS CT~ 5 Hel = inboard hinge moment, in-lbs

q = tunnel dynamic pressure, psf Se = elevon reference area, ft2 Ce = elevon reference chord, inches

(2) Compute outboard elevon hinge moment coefficient r _ He0

"eO ~ qSe„Ce He0 = outboard hinge moment, in- lb

(3) Compute total elevon hinge moment coefficient

Cu = C. + C.

^aT heI heQ

(4) Compute body flap hinge moment coefficient

H

C, = Hrf = body flap hinge moment, in-lb

hBF <ISBFCBF ’

Sgp = body flap reference area, ft^

Cgp = body flap reference chord, inches

(5) Compute the right wing panel bending moment and coefficient

M, . = ~ m2) lh m-. = inboard wing bending gage moment,

W am ’ 105 in-lbs

m2 = outboard wing bending gage moment, in-lbs

17

DATA REDUCTION (Continued)

BW = \ + NW in"lbs

B,

w-

= wing reference area,, ft

:z

Jw

-B,

w

qSijB

W REF

Bref = wing span, inches i = distance from m-, to m2 !1, gage, inches !

j

I = distance from mg to ex- posed wing root^chord, inches

(6) Compute the right wing panel torsion moment and coefficient

Tw = m3, in-lbs

ro-

wing torsion gage moment, in-lbs

Tt, = T,. + N,, (e_) “1307 W W “

, M1307

\i1307 3Suc

m

distance from m, to torsion reference center (X - 1307), inches 0

wing reference chord, inches

(7) Compute right wing panel leading edge, upper surface, lower surface and net pressure coefficients for the inboard chord- wise location (n = 0.436)

pw " p c- _ wLEi *o	i = 1
PLEi 1
, _ X ' Po PWUi 0	i = 2+13
c - ^ ' P°	i = 14+25
RWLi q
Cp Cp - Cp kT i KWUi KWLi	e.g., i = (2-14), (3-15),
etc.

(8) Compute right wing panel leading edge, upper surface, lower surface and net pressure coefficients for the outboard chord wise location (n = 0.771)

18

c

p

LEi

DATA REDUCTION	(Continued)
PW _ p WLEi o	i = 26
q
PW - P ui *o . q	i = 27+34
PwLi " Po q	i = 35+42

e.g. , i = (27-35), (28-36), etc

Angle of attack and angle of yaw were corrected for sting deflection. Gage interactions for wing bending and torsion were also applied.

The following reference dimensions and constants were used during this test:

Symbol	Definition	Model Scale	Full Scale
sw	wing reference area, ft2	0.6053	2690.00
bref	wing span, in	14.0502	9.36.68
s	wing MAC, in	7.1220	474.80
Se	elevon reference area, ft2	0.0473	210.00
ce	elevon reference chord, in	1.3605	90.70
SBF	body flap reference area, ft2	0.0304	135.60
:BF	body flap reference chord, in	1.2150	81.00
lrefx	Grbiter body length, in	[9.355	1290.30

DATA REDUCTION (Concluded)

lrefy	w.ing semi-span, in Gage Constants	7.0251	468.34
a m	distance from m-j to m2, in	0.6737	-
d	distance from m2 to exposed wing root chord, in	0.9448	-
em	distance from m3 to torsion reference point, in	0.7050	-

20

TEST :

fWT 282]

TEST CONDITIONS

DATE I 4 June 74

MACH NUhlBER

REYNOLDS NUMBER (per foot)

DYNAMIC PRESSURE (pounds/sq. inch)

STAGNATION TEMPERATURE (degrees Fahrenheit)

BALANCE UTILIZED:

CAPACITY:

ACCURACY:

COEFFICIENT

TOLERANCE:

COMMENTS:

TABLE II

Test l ,1&~70 TViJX.^82 1 6 at A SEf /run 'number collation summary l°AtE : ^ ^ ^

^DAT A SET IDENTIFIER

FI

CONFIGURATION

Tfo 5 i H2

PARAMETERS/VALUE

Se4

004

005

006

C07

008

009

010

Gil

013

014

015

016

0(7

£&z
O	O
O	e>
+4	+4

■H2 412

f4 j+l2 Ul'21+4

4-8 4-8

+s f a

+8	a	O	48
n	M	Bill
ii	4-8	48	in
H9S	412	II
-4	4-12.	412	SI

+8 +a

■44 +4

MACH NUMBERS ( OR ALTERNATE INDEPENDENT VARIABLE.

BP 10.90

O 15

19

2o

25

26

31

32,

35

108231

1.50

a or /S schedules

0 4o 4-8

FICENTS

PRE-SSI? I? £ DATA 1/4 DATASETS 13 4-Ky^ 68

= LW OUTBD

= UOBD

■ IDVAR'O) lOVAtf ’(2) 'ND

U4 tWBo

TEST RUN NUMBERS

TABLE II. - Continued

TEST : XA70 TVUT 2QZ

DATA SET IDENTI FI E R
RF70I9
IBBS
L	09ll
lUE^I
	023
	024
	025
	OX
	Oil
	023
I	029
	ObO
	63 1
'	032
	033
	034
II	C35

DATA SET/RUN NUMBER COLLATION SUMMARY

DATE : 2S M&Y \974

CONFIGURATION

Ti ZS

schd.|parameters/valuesS NO-

OF

o€4 Iruns

00	+8
+12	+12.
CO -+	+8

O

13HH

+K2

■\-A I +4

+ 8+8 +8 1+8

+8 +8 j +8

0 c o o

MACH NUMBERS ( OR ALTERNATE INDEPENDENT VARIABLE )

M2 1 11.241 I/.S6

£>4

<65

66

67 '

68

69

a or jS

SCHEDULES

CQEFFICENTS

= IM OUT©

EM CUTBb

TEST RUN -NUMBERS

TABLE Ii. - Conti hued ;

TEST;. Ik 76 WL.282

DATA SET/Ruf'i NUMBER COLLATION SUGARY

DATE : 29 UkV 1974

ID.ENTI FlEft	CONFIGURATION -	a	0	5ET	$22	~5eb	&4	OF f RUNS	6&f		Q$0.		1.12		1.24
5fTo57	6|Tl2SlP2PS	ter	-8	O	0	O	O		0						105
	r c3s		P=>			0																	167
	039		PlO	—											-								169
	040		Pll			1																	m.
	041		Pll																		115					■ s
	C42	‘foTis’Si Psffe .			O										■+•(0
	043															0		187		145		76		in
	044					♦4													138		144		79		H8
	045					E													188		143		78		115
	046					D	1	■	1	1	1	■	■	■	1				159		142		E3		114
	047					5*1 (•]	I	1	■	1	1	1	1	1	m				140		HI		77		10
j	' 048					BH	+4	4 4	+4	+4					94		10 1		132		(08
	<m					S3	l	l	1	1	1	1	l	V					135		\oo		131		109
	050					□	l		1	1	l			■					95		99		130		lio
	051			—		E	1	■	1			■		1					134			1	Hi	1	1 < 1
	052					E	■	1	1	1	■	■	1	1					96		97		133		112
	053		'			S3	4-8	4<S	46	*8					150		159	-	149		102.
1	054			1	1	44	48	+8		48		■	■		151		155		125		124

13

19

25

31

37

43

49

55

61

AW¥A

75 76 B

i gSBE : cm , zsm

L 1...1

a or /?

SCHEDULES

o LC&) z ~~ ^ 8s * £?;.

k a!

i-4—l .

coefficients

■ •tit

I 1 1 1--1-

tm

J — L

_ IDVAR(I) 1DVAR (2) NDV

Qg> - U4 OOT&O &2Z - LM IMBD

QU l>o6& ECA* EH COT&D

*■"" * ' ,,|l'-“ -- - - - -III ■ Ml ■ Mill “

TEST RUN NUMBERS

TABLE JI. - Concluded.

TEST RUM NUMSERS

TABLE III. - MODEL 'DIMENS I ONAL -.DATA

/-'MODEL COMPONENT: } Attach Structure ATg ■

J

"'GENERAL DESCRIPTION : Aft- SRB/ET attach structure (3 member structure)

r- Model .Scale: 0.015

-./DRAWING NO: VL7 2-000106
! -DIMENSIONS: MEMBER		• FULL SCALE
#1	%	1515
	yb	+ 56
	7,b .	50
	XT	2058
	yt	± 158
	Z'p	450
#2	XB	151? .
	Xb	+ 76
	zb	18
	X>p	. 2058
	yt	160
	ZT	445
#3	XB	1515
	xB	+ 56
	zB	- 50
	X<p	2058
	yt	+ 158
	zT	_JJ2
ODiameter/ of Members:	TBD

MODEL SCALE

22.725

+ .840

.750

30.870

- 2.370

6.75

22.725 + 1.140

.270

30.870

2.400

6.675

22.725 + .840 - .750

30.870 + 2.370

5.250

TABLE III. - Continued.

MODEL COMPONENT: Attach Structure AT-jh

GENERAL DESCRIPTION : Left rear -orbiter/KT attach structure (2 member structure)

Model Scale: 0.015

DRAWING NO. VL78-000050

DIMENSION : MEMBER	FULL SCALE	MODEL SCALE
Xo	1303	- 19.-545
Yo		-1.440
Zo	253	3.870
X<p	1359	27.8B5
Yt	115	1.725
7t	510	7.650
02 XQ	1317	• 19.755
Y0	-96	-1.440
Zo	253	3.870
xT	2058	30.870
yt	115	• 1.725
Ztp	510	-Jk&O,
Diameter of Members: TBD

27

TABLE III. - Continued.

■MODEL COMPONENT;: Attach Structure AT-j g .

GENERAL DESCRIPTION: Right rear orbiter/ET attach structure (3 member -structure)

Model Scale-: 0.015