Document
NASA TM X-758
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eo& or /
TECHNICAL MEMORANDUM
X-758
ST ABILITY AND CONTROL CHARACTERISTICS
OF A 0.0667 -SCALE MODEL OF THE FINAL VERSION OF THE
NORTH AMERICAN X-15 RESEARCH AIRPLANE (CONFIGURATION 3)
AT TRANSONIC SPEEDS
By Robert S. Osborne
Langley Research Center
Langley Station, Hampton, Va.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
April 1963
WASHINGTON
~-~ y-{JW(j
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
TECHNICAL MEMORANDUM X-758
STABILITY AND CONTROL CHARACTERISTICS
OF A 0.0667-SCALE MODEL OF THE FINAL VERSION OF THE
NORTH AMERICAN X-15 RESEARCH AIRPLANE (CONFIGURATION ))
AT TRANSONIC SPEEDS
By Robert S. Osborne
SUMMARY
In order to determine its static longitudinal and lateral-directional sta-
bility and control characteristics at transonic speeds, a 0.0667-scale force model
of configuration ) of the North American X-15 research airplane has been tested
in the Langley 8~foot transonic pressure tunnel. The test range included Mach
numbers from 0.60 to 1.18, angles of attack from -20 to 20 , and angles of side-
slip of -5.1 and 0 • The results of the investigation including a summary of
some of the important stability and control parameters are presented without
analysis.
INTRODUCTION
As part of the wind-tunnel program required for the development of the North
American X-15 research airplane, a 0.0667-scale force model of the final version
of the X-15 (configuration )) has.been tested in the Langley 8-f'00t transonic
pressure tunnel in order to determine its static stability and control character-
istics at transonic speeds. Tests of this model at Mach numbers from 2.29 to 4.65
are reported in reference L The results of pressure-distribution tests of a
model of a configuration nearly identical to that of configuration ) at Mach num-
bers from 0.60 to 4.65 are presented in references 2 and). Other tests of force
models approximating configuration) are reported in references 4 to 7. Tests of
a force model of an earlier version of the X-15 (configuration 1) in the Langley
8-foot transonic pressure tunnel are reported in reference 8.
The model was tested at Mach numbers from 0.60 to 1.18, at angles of attack
0 0 0
from -20 to 20 , and at angles of sideslip of -5.1 and 0 • Drag, static lon-
gitudinal stability, and static lateral-directional stability were determined;
the effectiveness of the horizontal tail as a pitch and roll control and the
vertical tails as a yaw control was measured; and the effects of opening the
speed brakes on drag and static stability were obtained. The results of this
investigation including a summary of some of the important stability and control parameters are presented herein without analysis.
SYMBOLS Longitudinal data are presented about the stability axes and lateral- directional data are presented about the body axes for a center-of-gravity loca- tion of 20 percent of the wing mean aerodyn~c chord.
wing span, in.
b
drag coefficient, D/qS
drag coefficient at zero lift
CD,o
lift coefficient, L/qS
lift coefficient for maximum lift-drag ratio trim lift coefficient trim lift effectiveness parameter, per deg lift-curve slope, per deg rolling-moment coefficient,
CC
l
effective dihedral parameter,
c/3 ' per deg
rolling moment due to differential deflection of horizontal tail,
cC
l
00 ' per deg
a rolling moment due to vertical-tail deflection,
pitching-moment coefficient, My/qSc
static longitudinal stability parameter, pitch effectiveness parameter at constant lift coefficient,
per deg
yawing-moment coefficient, Mz/qSb
dC
n static directional stability parameter,
-- per deg
d13 '
yawing moment due to differential deflection of horizontal tail,
per deg
oC
n
yawing moment due to vertical-tail deflection, -- per deg
do
v '
Pb - p
base pressure coefficient, q C lateral-force coefficient,
y
c wing mean aero~namic chord, in.
D force along XS-axis, positive rearward, lb
lateral force, lb
L lift, lb
maximum lift-drag ratio
(LID)
max
M free-stream Mach number
moment about X-axis, in-lb
moment about Y-axis, in-lb
moment about Z-axis, in-lb
static pressure at model base, lb/sq ft
p free-stream static pressure, lb/sq ft
q
free-stream ~amic pressure, lb/sq ft
L-1655
R Reynolds number total wing area, sq ft S
X,Y,Z body axes
stability axes angle of attack of fuselage center line, deg angle of sideslip, deg differential deflection of horizontal tail when used as roll control, positive when left-hand surface has more positive deflection, (trailing edge down), deg deflection of horizontal tail when used as pitch control (taken as average of left- and right-hand surface deflections and positive when trailing edge is down), deg deflection of upper and lower vertical-tail surfaces, positive when trailing edge is to left, deg APPARATUS AND TESTS Model The X-15 is a rocket-powered resear~h airplane designed for hypersonic speeds at very high altitudes. It employs a 5-percent-thick low-aspect-ratio trapezoidal wing mounted in the midposition on a fuselage consisting of a body of revolution with large side fairings. The horizontal tail which has 45 sweep- back of the quarter-chord line is all movable for pitch control and is deflected differentially for roll control. The outboard panels of the upper and lower vertical-tail surfaces are deflected for directional control; the inboard panels are fixed and contain the speed brakes.
The 0.0667-scale force model of the North American X-15 research airplane used in this investigation was supplied by the contractor and was of stainless- steel construction. Photographs of the model are presented in figure 1, and dimensional details are shown in figure 2 and table I.
The model represented configuration 3 of the X-15. Features that distin-
guish this configuration from configuration 1 (ref. 8) include an increased
fuselage diameter, shortened fuselage side fairings, increased leading-edge radii on wing and horizontal tail, wing shifted forward 3~6 inches (full scale), horizontal tail shifted rearward 5.4 inches (full scale), a larger vertical tail having 10 full-wedge airfoil sections with the total exposed area distributed
about 55 percent above the fuselage and 45 percent below, and reduced speed-
brake area. The contractor's code designation for the model tested was
B4W2X14H9VU5JU2VL7JL2'
The movable portions of the upper and lower vertical tails and both
horizontal-tail panels could be actuated remotely while the wind tunnel was in
operation. The speed brakes were maintained in the closed position or were
opened 35 relative to the closed position as indicated in figure 2. The speed-
brake hinge lines were located at the speed-brake leading edges and had 0
sweepback.
Tunnel and Model Support
The tests were conducted in the Langley 8-foot transonic pressure tunnel
which is a single-return rectangular slotted-throat wind tunnel having controls
that allowed for the independent variation of Mach number, stagnation pressure, temperature, and humidity.
The model was attached to a sting support by an electrical strain-gage bal-
ance located inside the fuselage. The sting support was cylindrical for 2.4 base
diameters downstream of the model base and had a diameter of 0.55 base diameter.
At its downstream end, the sting was attached to an arc-shaped support strut
which spanned the tunnel vertically. This support strut was rotated to obtain
changes in angle of attack; the center of rotation of the system was near the
model in order to minimize overall vertical motion of the model. Variations in
angle of sideslip were obtained by insertion of properly angled couplings in the
model support system.
Measurements and Accuracy
Model forces and moments were measured by a six-component internal strain-
gage balance. They were converted by automatic electrical computing equipment
to lift, drag, and pitching moment about the stability axes and to lateral force,
yawing moment, and rolling moment about the body axes. (See fig. 3.) The center
of gravity was located at 20 percent of the meav aerodynamic chord based on the
total wing area. (See fig. 2.) At a Mach number of 1.0 and a dynamic pressure
of 784 pounds per square foot, accuracies of the coefficients are estimated to
be:
±0.01
±0.002
±0.002
. . . . . . . . . . .
±0.0005
. . . . . . . .
±0.0005
C . . • • . . . . .
±0.005
y The angle of attack was set to within ±O.lo by means of a pendulum-type attitude indicator located in the nose of the model. The angles of sideslip were determined to within ±0.2° by means of a calibration of sting and balance deflection with respect to model lateral force and yawing moment. Horizontal- and vertical-tail deflections were measured remotely by means of differential transformers attached to the control-surface linkages and are estimated to be accurate within ±0.2°. Speed-brake deflections are estimated to be accurate within ±O.lo.
The Mach number was determined within ±0.003 from a calibration with respect to the pressure in the chamber surrounding the slotted test section.
Base pressure coefficients were determined from an average of measurements taken on the upper and lower portions of the base and are estimated to be accurate within ±0.005.
Tests The complete model was tested with horizontal-tail deflections for pitch and roll control, with vertical-tail deflections for yaw control, and with the speed brakes open and closed. The model was also tested with the horizontal tail removed, with the lower vertical tail removed, and with both vertical tails removed. The detailed test program is indicated in table II.
The test range included Mach numbers from 0.60 to 1.18, angles of attack 0 0 from _20 to 20°, and angles of sideslip of -5.1 and 0 • The tests were con- ducted at a tunnel stagnation pressure of approximately 1 atmosphere. The average test Reynolds number based on the wing mean aerodynamic chord varied from approximately 2.2 X 10 to 2.8 X 10 over the Mach number range. (See
fig. 4.) For all tests, O.l-inch.,;wide boundary-layer transition strips con-
sisting of No. 120 carborundum grains were installed along the 10-percent-chord lines of the wing and tail surfaces and at 10 percent of the fuselage length.
Corrections Tuni.l.el-boundary interference at subsonic speeds is minimized by the slotted test section, and no corrections for this interference have been applied. No corrections are necessary for the effects of supersonic boundary-reflected dis- turbances since they are negligible for Mach numbers up to approximately 1.03
(ref. 9), and the reflected disturbances pass well downstream of the base of
the model at a Mach number of 1.18.
With the use of the measured base pressure coefficients (shown for thI:'ee con- figurations in fig. 5), the data presented have been adjusted to an assumed con- dition of free-stream static pressure acting over the base of the fuselage. No sting-interference corrections have been applied. However, as indicated from the results of reference 10, errors in the drag data due to the presence of the sting,are estimated to be small and errors in the other coefficients are prob- ably negligible.
RESULTS AND CONCLUSIONS The results of an investigation of the stability and control characteristics of a 0.0667-scale model of the final version of the X-15 research airplane are presented in the following figures: Figures . . . . . . . .
Basic longitudinal data as functions of C ••• 6 to 15
L
16 to 24
Basic lateral-directional data as functions of ~ Longitudinal stability and control parameters •••••• 25 to 27 Drag and maximum lift-drag-ratio parameters .• .
Lateral-directional stability and control parameters
. . . . 29 to 33
A more detailed index of the results presented is sbown in table II.
The data indicate that the configuration investigated has generally satis- factory static stability and control characteristics at the Mach numbers and angles of attack tested. Notable exceptions, however, include a region of neutral longitudinal stability at low negative angles of attack at Mach numbers from 0.60 to 0.95 and excessive positive dihedral at high angles of attack at Mach numbers above 0.60.
Langley Research Center, National Aeronautics and Space Administration, Langley Station, Hampton, Va., November 8, 1962.
REFERENCES
1. Franklin, Arthur E., and Lust, Robert M.: Investigation of the Aerodynamic
Characteristics of a 0.067-Scale Model of the X-15 Airplane (Configura-
tion 3) at Mach Numbers of 2.29, 2.98, and 4.65. NASA TM X-38, 1959.
2. Osborne, Robert S., and Stafford, Virginia C.: Basic Pressure Measurements
On a 0.0667-Scale Model of the North American X-15 Research Airplane at
Transonic Speeds. NASA TM X-344, 1960.
3. Hodge, B. Leon, and Burbank, Paige B.: Pressure Distribution of a 0.0667-
Scale Model of the X-15 Airplane for an Angle-of-Attack Range of 0 to 28
at Mach Numbers of 2.30, 2.88, and 4.65. NASA TM X-275, 1960.
4. Lopez, Armando E., arid Tinling, Bruce E.: The Static and Dynamic-Rotary Sta-
bility Derivatives at Subsonic Speeds of a Model of the X-15 Research Air-
plane. NACA RM A58F09, 1958.
5. Tunnell, Phillips J., and Latham, Eldon A.: The Static and Dynamic-Rotary
Stability Derivatives of a Model of the X-15 Research Airplane at Mach Num-
bers From 1.55 to 3.50. NASA MEMO 12-23-58A, 1959.
6. Dunning, Robert W.: The Control Characteristics of Two Preliminary Models
of the X-15 Research Airplane at Mach Numbers of 2.98 and 4.01 •. NASA
TM X-212, 1960.
7. Penland, Jim A., and Fetterman, David E., Jr.: Static Longitudinal, Direc-
tional, and Lateral Stability and Control Data at a Mach Number of 6.83 of
the Final Configuration of the X-15 Research Airplane. NASA TM X-236, 1960.
8. Osborne, Robert S.: Aerodynamic Characteristics of a 0.0667-Scale Model of
the North American X-15 Research Airplane at Transonic Speeds. NASA
TM x-24, 1959.
9. Wright, Ray H., Ritchie, Virgil S., and Pearson, Albin 0.: Characteristics
of the Langley 8-Foot Transonic Tunnel With Slotted Test Section. NACA
Rep. 1389, 1958. (Supersedes NACA RM L5lHlO by Wright and Ritchie and
RM L5lKl4 by Ritchie and Pearson.)
10. Osborne, Robert S.: High-Speed Wind-Tunnel Investigation of the Longitudinal
Stabili ty and Control Characteristics of a l~ - Scale Model of the D-558-2
Research Airplane at High Subsonic Mach Numbers and at a Mach Number of 1.2.
NACA RM L9C04, 1949.
TABLE I.- DIMENSIONS OF 0.0667-SCALE MODEL OF CONFIGURATION 3 OF
NORTH AMERICAN X-15 RESEARCH AIRPLANE
Wing:
Airfoil section . • . • • Modified NACA 66-005
Total area, s~ in. 127.728
Exposed area, s~ in. 66.816
Total span, in. 17.87
Exposed span, in. 11.968
Total aspect ratio 2.50
Exposed aspect ratio 2.15
Leading-edge sweepback, deg • • • • • 36.75 Quarter-chord-line sweepback, deg ••••
25.64
Trailing-edge sweepforward, deg
17·75
Root chord at center line" in. 11.914
Exposed root chord, in. 8.8
Tip chord, in.
2.383
Total taper ratio • • • • • 0.20
Exposed taper ratio • • • • • • • • 0.27
Mean aerodynamic chord based on total area, in. • • • • 8.207
22.76 Longitudinal distance from fuselage nose to total wing 0.20c, in.
o Dihedral, deg . • • • • • • • • • • • •
Incidence, deg •••••••• • • • • o
Horizontal tail (in plane of surface):
Airfoil section • Modified NACA 66-005
Total area, s~ in.
73.850
Exposed area, s~ in. 32.832
Total span, in. 14.978
Exposed span, in.
9.008
Exposed aspect ratio . • • • • 2.48
Leading-edge sweepback, deg
. . . . 50.58
45 Quarter-chord-line sweepback, deg • • • • • • • • • • •
19.28 Trailing-edge sweepback, deg
Root chord at center line, in.
8.175
Exposed root chord, in.
5.6
1.686 Tip chord, in.
Exposed taper ratio • • • •
0.30
Mean aerodynamic chord based on exposed area, in. ••••••••••
3.986
Hinge line, percent exposed c . . . •. ...• . • • .
Longitudinal distance from total wing 0.20c to exposed tail
0.25c, in. • • • • • 12.461
Di,hedral, deg . • • • • • • • . • •
-15
Upper vertical tail (exposed panel):
Airfoil section • 10 wedge
Area, s~ in. 26.075
Span, in. . . .
3.669
Aspect ratio
0.52
Leading-edge sweepback, deg •
Trailing-edge sweepback, deg o
TABLE 1.- DIMENSIONS OF 0.0667-SCALE MODEL OF CONFIGURATION 3 OF NORTH AMERICAN X-15 RESEARCH AIRPLANE - Concluded Root chord, in. 8.171 Tip chord, in. 6.053 Taper ratio 0.74 Mean aerodynamic chord, in.
7.153 Longitudinal distance from total wing 0.20c to exposed panel 0.25c, in. 10.309 Movable portion Area, S'l in. 16.848 Span, in. 2.482 Root chord, in.
7.49 Tip chord, in. 6.053 Hinge line, percent exposed panel c Speed brake (one side) - Area, s'l in. 3.514 Chord, in. 2.678 Average span, in. 1.308 Lower vertical tail (exposed panel): Airfoil section 10 wedge Area, S'l in. 22.476 Span, in. 3.085 Aspect ratio 0.42 Leading-edge sweepback, deg • Trailing-edge sweepback, deg
o
Root chord, in. 8.171 Tip chord, in. 6.4 Taper ratio 0.78 Mean aerodynamic chord, in.
7.321 Longitudinal distance from total wing 0.20c to exposed panel 0.25c, in. 10.144 Movable portion Area, s'l in. 12.6 Span, in.
1.881 Root chord, in. 7.486 Tip chord, in. 6.4 Hinge line, percent exposed panel c Speed brake (one side) - Area, s'l in.
3.514 Chord, in.
2.678 Average span, in.
1.308 Fuselage: Length, in.
39.36 Maximum depth, in.
3.733 Maximum width with side fairings, in.
5.868 Maximum width without side fairings, in.
3·733 Fineness ratio without side fairings 10.54 Base diameter, in.
3.197 TABLE 110- INDEX OF FIGURES PRESENTING RESULTS Figure Longitudinal characteristics of:
Model with and without horizontal tail. ~ = 0°; varying De •••• 6
Model at negative angles of attack. ~ = 00; De = 0° and 10°
Model with and without vertical tails. ~ = 0° .••••• 8
Model with speed brakes open and closed. ~ = 0°; De = 0° .••
Model with speed brakes open and closed. ~ = 0°; De = _10° • • • • • 10
Model with varying De and with speed brakes open and closed. ~ = 0°;
Da = 0°; Dv = -7.5° • • • • • • • • • • • • • • • • • • • • ••
Model with varying De and with speed brakes open and closed.
oa = 20°; 0v = 0° .. . . . . . 0 • 0 • • • • 0 • . .
Complete model. ~= 00 and -5.1°; De = 0° and _10° •
Model with speed brakes open. ~ = 0° and -5.1° .••• 14
Complete model. S = 0° and-5.lo; Ov = -7.5° •••• 15
• • • •
Lateral-directional characteristics of: Model with speed brakes open and closed.
De = 0° and -10°; DV = 0° and -7.5° •• • • • • • .'. 0 •
Model with speed brakes open and closed. ~ = -5.1°; Da = 0°;
oe = 0° and _10°; 5v = 0° and -7.5° ••••••• 0 • 17
Complete model. ~ = 0° and _5.1° .••••••••• 18
Model without lower vertical tail. ~ = 0° and -5.1° •••.••• 0 •
Model without upper and lower vertical tails. ~ = 0° and -5.1° 20 Model with speed brakes open. ~ = 0° and -5.1° ••• 21 Model with lower speed brakes open. ~ = 0° and -5.1° 22 Model with speed brakes open and closed. ~ =0°; Da = 0° and 20°;
De = 0° and _10°; DV = 0° ••• 0 ••••• 23
Complete model. ~ = -5.1°; oa = 0 and 20°; Be = 0° and _10°;
DV = 0
°
Summary curves: Variation of lift-curve slopes with Mach number ••••••••••• 0 ••
Variation of static longitudinal stability parameter with Mach number. 26
Variation of longitudinal control parameters with Mach number •••• 27 Variation of drag and maximum lift-drag-ratio parameters with Mach number . • • • • • • . • • • . . • • . • • • • . • • • • • • Variation of directional stability parameter with Mach number.
Variation of effective dihedral parameter with Mach number Variation of lateral control parameters with Mach number.
Variation with Mach number of yawing moment due to vertical-tail deflection
• • • • 0 • • • • • • • • • • • • • • • • • • • • • • 32
Variation with Mach number of rolling moment due to vertical-tail deflection
• • • 0 0 • 0 • • • • • • • • • • • • • • • • • • • •• 33
tunnel.
pressure L-57-5411 transonic 8-foot Langley in installed X-15 of model scale 67- o.06 of Photographs 1.- Figure I-' f\) '(j
]
() Q o o I H J,
t
5.54 4.95
1-
I
noted.
~
....,
~
I~
==-~
otherwise
\
unless inches in are
.20c
dimensions All
--
•
open.
brakes
c:::'\:::::::==-
speed
------
---
with
~ ~~-----39.36
r-----: I I
X-l5 of model ~ O.0667-scale of Drawing
17.87 2.-
Figure I-c.
f-' +"
Relative wind
\
/3
L
x
X _<E--L------
~~-------+---------- 0
S
Relative wind
z
Figure 3.- System of axes. Arrows indicate positive directions.
1.2
inches.
8.207 I.
c on ---- based r--
1.0
---
M
Reynolds number
~
.9
test of number, -
~
number
Mach
~ _._-- Mach
.8
with
V
./
~ Variation
.7
~ ..
4.-
/
Figure
./
~ '-----
.6
3.2
2,8
2.0
..
~ E ;::, c (f) o ;'2.4 Q)
n::: ..c "'0 n::: ~ .2 0 Complete model Vertical tails off <> Complete model ,brakes open
o
M=O.60 ~ I
I~~o
~ v o M=O.BO .80 o M=O.90 'r-- :--0
~
.90
---, ...(.
V
.....-
--- ':)
-,. r--
--
M=O.93
.93
M=O.95 I---r:
--
5l
"'.9~
o m
I
o -
M=1.03 --r r---.
-
I'--r
~
r---
t:---....
~.
---,
r- ~ . 1.03
....., -,.
>--- ~ ~
o
-
M=I.IB -C~ -.2
- h
~ -0 1./8 -:-0 "---< >- .J$} -.4
-4 o 4 8 12 16 20 24
Angle of attack ,a,deg Figure 5.- Base pressure coefficients for complete model and for model without vertical tails.
Surfaces undeflected unless otherwise noted. ~ = 0°.
jt>- Se,deg I- .4 Q Hori lontol loil off t- ~ \-A.. i"-- l-
r--
t--- ~ 0 -10 .3 I- <f- c, E I-- b-- -15 ~ U I- D -20 '"Or--- \"-,
'" ~
.~ .2 u ~ 1\
;;: """
"- ;; o I u I~ ~
""
c 01-- 1"-0
E 0
r<;;
o ra !~
~ i"--ln "- c • I '" - :E I"- ~ 1"- 0:: -.2
'"
-.3 i'..
~ -.4 -.5 ~ /' l-0 19': /"/. V V '" 16 i/,< V -8 ~ ../ ~: u 12 /' V;: / / / .E '0 I/.': v I V:: 'S 8 V // V .0 ,j V LV V:: ./.., /' 711 l# 7 /,
/' l/ 7
o 368 ~ './ V
i
v. / :?" 7 1 !
-4 32~ I I /It. I
28 e
~/ / Cl II II f / II II 1.1 ill
~ m-
~ 1/ II rl
...) '/ ~ f/
'" 12
{P ID- \.Jl 1""- v- IP 1'-..
""
"0. V V 1.4 -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 , Lift coefficient ,C for Cm and" L-' _--'-_-'---_L--...JL---L_--'-_--'--_-'---_-'--_L---.l._--' ! ! ! I I I L I .8 1.4 -.6 -.4 -.2 0 .2 .4 .6 1.0 1.2 1.6 1.8 Lin coefficienl,C for Co L (a) M = 0.60.
Be and of model without horizontal Figure 6.- Longitudinal characteristics of model with various tail; other surfaces undeflected. i3 = 0°, ·5 A- 8 ,deg e r-- .4 o Horizontal tail off
r---
0 r- '"0---t)...
i'-- 0 -10 .3 r- ""I'-- -15 E
'" '"
u "- co .2 ~ " ~
~
I \ [\, o " " p- 1\
---
~ 0 IV" 1"'- IO-C E f'-o ~
"
-"
o ,,~ I'-- ~ - I '" .
co ~ :c " ii: ...,2 I"- q -.3
"
-,4 'E
"
"- -.5 i"- f!
V V V 10 ~ 1:/ IL V V ~'/ IL ~ ~ V V j II 1 k:; r/ 1/ V ~V j/ V V
v:: #
V VI! !
k:: ~ '"
36 ~.
.
jfl
J? -""~
.~ " !5" 1/ I/~ ~ o 32 ~ V 8 k:: ~I/ ~ II -"'" '" , -4 28.5 [i /
lLW
II; V 'l / 17 L / / / II,!'
/
"
I"- 1/ A- ~ .1 '- V f\, i'>-- ,-"'"
V
'-..
V V ...0/ .()4 -.6 .. 2 0 .2 .6 1.0 -.4 .4 .8 1.2 1.4 1.6 Lift coefficient,C forCmonda I L I I I I I I I I I I -.6 -.4 -.2 0 .2 .4 .6 1.0 1.2 1.4 1.6 1.8 ·8 Lift coefficient ,C for CD L (b) M = 0.90.
Figure 6.- Continued.
.5 8 ,deg e A - 0 rbrizontal tail off 0 -
I'<
-10 --- .
.3 - 6.
I"< -15 E "-.
'-' ,.,.
.2 c Q) ro.. 6.
'"
~ ~ .1 Q)
"'"
c.> In.
- 1:'
""
I~ E 0
"'-( I'--t o
--
"
E I'----
--
'V tb -,I
--
c: I'r-l :c ~ -.2
'"
'"
Ig -.3 -,4 -.5 64
'"
f".-. I II V V ~ .....:: V I
""" 16 52
P' C> "I / ./' ./' ~ ~ ./' '/ V
/. !
.=: 12
./ [:/ c.> /I, I /' ~ V IL:: VI II '5 I-"" V ~ i/, o III '-'
V c::: ~
!
V P'
II 40l
VI'" V 1/ 36'~ ,./ V
r« I
C>
/. ,L t
-4 32~ Ii I
1/
1..
'/ p II / ,/
?J
!j V /
iL
f1 / if p j.
t----- ./ 'x .~ b", ~ ""'" -.6 -,4 -,2 0 .6 .8 1.0 1.2 1.6 1.8 .2 .4 104 Lift coefficient, CL for C and a !
m I I I I I I I I I I I I 1.6 -.6 -.4 -.2 0 .2 A .6 .8 1 .• 0 1.2 104 1.8 Lift coefficient ,C for Co L (c) M = 0.95.
Figure 6.-. Continued.
.5 8e ,deg '-- .4 0 Horizontal tail off - I-- --...,.
<> -10 - .3 "'- --..., A -15 ""- ,J .2 ~ Q.
'E Q) '(3 I ~ i'-.
""- Q) '.;-:- o
"'-
" 0 """
1""- ---.
'E "--c ~ P--.
Q) E ~ ro- "'-
o _.1 "-
--
~ 1,\ ~ ~b 0> c:
f"-
~ ~ -.2 i'-.
"-
0::
b "-
-.3 "0
"'-
~ -.4 68 ~ ~ -.5 64 I II -.6 -(j>, '1'/ I¢ I 'I I L'..
:;.-- V d /II I ~ V 1/ ./' V /'
/1 c\
I?'
./.6 V I II I ~V 'i III ./.
V r; I ~ 1/ .,./ Y' 11 Q)
LV /1
~
g.4
V ~ /, / <!
.,./
V 111//
o V V / ~ / I liII .L' -4
IF/
V II
/ II
fj ~
~ L /
./.
"'- 1/ "'l-
./
-...; ?"
p::- rY: o .8 1.0 1.2 104. 1.6 1.8 ! ! ! I I I ! I I I I -,4 .8 1.2 104 -.2 0 .2 .4 .6 1.0 1.6 Lift coefficient, C for CD L (d) M = 1.03.
Figure 6.- Continued.
.5 Be,deg .4 C- o Horizontol toil off ~ <) <) -10 - .3 /).
-15 1'0-.
'-- D -20 r-....
.2 E I~ c" i'---,
"" ~
Q) .1 '<3 n. ~ I~ ~ 0- Q) "- r::::::: ::",., 0 I" <.> -C r-- ~ --<0..
E Q) -{~ '\,.
~ ~ E
-.1 --
"-.
'-....,
"'-
~ 0>
to.. "'-
c: -.2 :c .!:!
"'-
u:
'"
~ -.3 TI...
'"
-.4 "i:l..
i"--.
-.5 "0 -.6 60
r
>j '/' l' 20 52 /'
/P: ....0 m III
,/
~ /"' I II [I
16 48
r::r
~ /. I I V ~ V NI ~ 12 V f'" V il/'d ".
il v /::: 'l
:g 8
.//. V' IN I '0 ./ o ,/ k;:: ~/; tl 36~·
f 4
~
v m
/.
~
It I
""'~
o V" 32~ ,/ II II /.
0> V
V II I
~ -4 28~ J P V Ifj [I / l
i. /
!
V I{( /"
1#
v
I"-- /
.s:y f-o.
../ 0: t-- .J'1" ;:r; -.6 -,4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 Lift coefficient,CLfor C and a m I I I I I I I I -.6 ,4 .6 .8 1.0 1.6 1.8 -.4 -.2 0 .2 1.2 1.4 Lift coefficient, C for CD L (e) M = 1.18.
Figure 6.- Continued.
I
10-
f+-
o 0
M=O.80 ro::: --c p- I--- I'---- ---r fu...
M=O.93 "'",- ......."
""-- I - -.
'--t <= ~ Q)
"'"
E
1"-
~ -.2 g' Q
"\
~ -.3 '"
a:: M
""
-.4 .80
'" "-
""
-.5 "-...
.93 .80 V .93 .64 16 V ~ V .60 V 1/ .. 80 .93 V L .56
r
/ ./ / ./ / .52
V / /
/ / II j .48 ~=O.80 V V V I I V o .44 M=O.93 7'
/ 1/
V .40 I I rj, / .36
q
/
/
~ .32 / / '0
~ .28
/ /
'" e
Cl .24
d /
II .20 /
/
.16
1/ /
II ci .12
/
V .08 V Q .n V I--< .04 .-E o ~=O.80 M=O.93 .6 1.8 2.0
9. 6 -.4 -.2 0 .2 .8 1.0 1.2 1.4 1.6
.4 Lift eoefficient,CL (r) M = 0.80 and 0.93; = 0°.
°e Figure 6.- Concluded.
.3 8 e ,deg '---- ~ .2 ( o 0 - 0 10
:~
i'--
§
""
-C'l 1'0.
~ 0 -0
---
'"-
~
g' -.1 I"--,b.
'"
:E .ld ~ 0::: -.2 P-- '-;J-....
-.3 4· /r-' V ./ V ,/ / / V V ./ / d V
V
_d / -16 ,/ / ./ 0' .44 c \ .40
\
q .36 o \ u
\ \
]l .32 :~
\
~ \ 8 .28
'\ \
l
.24 \ \' \ \ .20 1\ Q, \ .16 f\ \ .12 1\ '\ I\- ,08 "- V r--.,.
.04 ~.6 -1.4 -1,2 -1.0 -.8 -.6 -,4 -.2 0 .2 .4 .6 .8 Lift coefficient, CL (a) M = 0.60.
Figure 7.- Longitudinal characteristics of model at negative angles of attack. ~= 0°; Be = 0° and 10°; other surfaces undeflected.
.3
'"
8 ,deg e I-- .2 0 0 'c:L I-- o 10 ~ "- ~ .1 ':::x .~ --cJ'-----, ~ 0 ~-.....(
c "
."-c
E -.1 '"
~
'"
1-.
""-..
~ a.. 1"-1: -.3
r---
:D-- 1'--10 -.4 V V O"'V V o V V d d
-4 .g
./ ./ ..: ---,::,: ,/' V 8 ~ V
V
'/ / -12 ~ ,/ '/
.52 :w
'r/
r/ ,/ Q / .48 ./ ,,/ ~ -20 ,44 \ i
\ \
,40 \ ,\ .36
\
Ii.
8' .32
i\ '\ \
~ .28
1\ 1\
i \ \
c> .24
E 1\ 1\
o
\ \
.20
1\
\
.16
\
I\, \ .12 ,/ 1,\ r".
V ~ = .08 ---.
I""'" I'a. .J.
.04 il l.6 -1.4 -1.2 -1.0 -.8 -.6 -.4 -.2 0 .2 .4 .6 .8 Lift coefficient,CL (b) M = 0.90.
Figure 7.- Continued.
·3 Q 8 ,deg e .2 t- o 0 ['Q
'"
t-
J
o 10 ~.
I 'u
"'" "In h-
P- kl-- ] 0
i'-- r-
--
-E~OC: "In -.1 i'...
, 0> .\; [R ~ -.2 ~
-
1"'- t-- r-kc -.3 t--tD- r-~n
-,4 --
V
V
V -/ o V /' 0> V ./ -4 ~.
c.
V V u V "'" • CY' -8 ~ / / /
1/
'"
-12 !
l-O V V d V lL:: .52 ~/ In" -20 ,48 1\ \} .44
\\ \\
,40 \ \ 0.
\1\
u
"* .32
1\ Ib
~ \ \
§ .28
1\ ~ o \
'\
.24 'to
1"-
.20
\\
\
.16 \ p "\
1"'-
.12 /
~ "-
j.EY In.
.08 "'-
.CJ....
./ ,....".
.04 .9 1 .6 -1.4 -1.2 -1.0 -.8 -.6 -,4 -.2 0 .2 ,4 .6 .8 Lift coefficient ;CL (c) M = 0.95.
Figure 7.- Continued.
.4 p, "- 8 ,deg e - .3
"-
- o 10
" t------
Ic:r:: '0..
I ,"---
----
""- --0
'"
---
----:.
i'"
'"
I b.
'"
"--.
-.2 "-- :J.--.
"n -.3 :l-.....
-- 0
-.4 V /' ./ ./ o /' V g' -/ 4 "0_ .60 t!_ /' V ./ ~ ~ -8 C .56 / /
\
'0 .91 ,El 12 go .52 <t \ 1/ 1,-/ V \ .48 ./
lX
V I~ ~ .44 \ \ \ .40 \ '\ \ .36 \ r o <.)
\
~- .32 \ '0 \ !i: \ 8,28 \ \ \
~ ~
.24 '\ \ \
\
.20 1\ r\ .16 "- "- 1/ V
"-
i'-- .12 -u "- b 'y) .08 .04 .9 .6 -1.4 -1.2 -1.0 -.8 -.6 -.4 -.2 0 .2 .4 .6 .8 Lift coefficient, C L (d) M = 1.03.
Figure 7.- Continued.
.3 8 deg e• ~ o 0
E .2 -
o 10 "-- <.)
~. '----....
-n Ti .1 '-I'---""
'"
~ 'Ct---- 8 0
"
"',,-
!
I"- ""10 g -.1 '" , "-- 1""- ~ r--...
[-.2
r---
""" -.3 '>./
"" V
"1 V -.4 o V ./ /'
V
V rl c/ V V ./ L/ ./
V
/' .56 Y 0' .52
\
.48 "\
\
.44 \ \ .40 \ 1\ ~ \ .36 o 1,\
\
<.) •• 32 \ \ C .!!1 u \ ~ .28 \
\
~ .24 \ ~ 1\ .20
\
\ .16 "-\ 1""- ./
"-
.12 t!- V
"'"
'"
'-r.
.08
---
.04 9 .6 -104 -1.2 -1.0 -.8 -.6 -.4 -.2 o .2 .4 .6 .8 Lift coefficient. CL (e) M = 1.18.
Figure 7.- Concluded.
.2 E o Complete model I--- I .,.: o Lower vertical tail off
°
c: 10- I--- OJ -u <> Both vertical toils off '(3 () I-
<;:: t-c t--
h
o
'1;; jW"- t""--t-- ~ ]'--.: ~ "E I '" - E
~""
~ "\ ~
g, -.2
:c "~ ~ 0:: -.3 ""'~ ~.
-.4 1"'<> ~ k;: ~ I 6 j7V ~ .52 0>
If
2 ~.
I b:7' "' .
~ . 48 "'" u I:?'
gil
~ 8 ~
~ III
,44
VII
~~ 17"
oil
~ ,40 ~ II.
o
VII
~ .36 tp ,.&
Jill
-v 4 o !!
0 •• 32 I(/J/..
~ u ~ .28
II
e .24
o
lfl
.20
dll
.16
7 f7
/. J .12
W II
W td'
.08
~ '/
h-
1d::1--
I?' V
.04 -u IQ, j»' 1'--. b- o 1.0 1.2 1.4 1.6 1.8 -.6 -,4 -.2 o .2 .4 .6 .8 Lift coefficient ,CL (a) M = 0.60.
Figure 8.- Longitudinal characteristics of model and of model without vertical tails, surfaces undeflected.
~ = 0°.
.1 LJ..
br- o Complete model
-
""- -a... o Lower verticol toil off b-, """'<: ~
o
<> Both verticol toils off -
r<= E I"--- ~ t--..
u.
K:: E ~~ .~ -.1 "'i~1"-.
~ lh
~ -.2
E ~ ~ c: ~ ~ -.3 , ~ CI <::
"
~ ;s?; ~ -,4
"
'c i:t ~ 0 ::---El -.5 i"'--- -.6 ~ I 6 17"" h .60
P
~ I 2~
p-
d' ..0 I .56 u· ~ lff.
8g o V
h VII
.52 '0
~ r1
p- 1/ l...'i .48 ~I"" VI.J..
o
k:;; IP '{1 .44 _1/ ~
VLL
.40
r1
/I
0.
fPd
u
JJL
.~ .32
"
II
'1
~ 28
",' e o W .24
.l 1
~< .20 II /
f
.16
A L
f,V .12
~ L
V/ /
.08
tL .&'L /
0-: r--"
'" t--.. fa' /"
.04 1/" (Y"
'"
.Q6 -,4 -.2 o .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8
Lift coefficient, CL (b) M = 0.90.
Figure 8.- Continued.
.1 j"8- o Complete model
- t--
- ~ o Lower verticol toil off E I'D..
~.
U
-
0 <> Boih verticol toils off ~ '-....
"E ~ .~ u '-....
:J.....
-.1 ....
"-.
....
OJ '0.
U ~
""
-.2 c: .'c
'"
-
~ OJ E ro,: 0 ~'\ -.3 E I '\ ~ 0> c: .c: f'- ~ -.4 ~ .):~ CL ~
-.5 ."
)J ~.
-.6 'V ~ ./.
.64 ~ I 6
V"
/- /
.60 'P
~ IJ?
I V/ ~ ~ .56 ~
h /
/fJ
~ .52 'P"
f/
~ ?" .
..0 /
,48 ~F"
/11
o 7"
//
~ ,44
l& /
-4
#/
,40
If!
/ "1
8' .36
II II
+-'" c:
II
OJ .32
I I
~ '" 0
:j I I
~ .28
Q II
Cl
1901 I
.24 II .
II /
.20
II
1//
/
.16
I s£ /
t( .12
~ l?
t/ /
.08 '----..
--::::: V
V
~ v
.,..;:v
~ .04 (y
o .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8
Lift coefficient ,CL (c) M = 0.95.
Figure 8.- Continued.
.1
-- o Complete model
r0-
- (""" o Lower verticol toil off F-
to """e
E 0 o Both verticol toils off
-
u [0'- i"c f'.- .,: c ........
['...., ~ "G -,I ;;:
"
't o I~ .:: -.2
"'"
c ~ ~ Q) E t3:0i">..
~ -.3 1 ~ 0> C ~~ ~ -.4 &..'" a:: , -.5 1"'\
"
"\ -.6
"
I"\p
.68 ~ .64 p~
I
- II IV .
. 60 F ~ f(i i.e ~ .56 16 !""
~ II I
V
~ ..1 /
.52 ~
~ J.11
~ ~ I I
.48 P'" ~ Q) lai'fP'
-.ell
0,44 4"0> c p-
(.) _L
..:. I «
~r" 1:=- 'JI~ .!!l 40 o ~' P'"
h ..!y
Q)
~ IfJ
/
0> .36 4 '(L e o j I.
.32 VIII ~ .28 Vj Ii.
/ .24 11/
/
!
.20
rL L
lP/
/ .16 V
L:J
[.P / V .12 ./ V
/
r- ",/ D,
IO- /
.08 ,.......
/
.......
w
. 04 ~6 -.4 ...,2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, CL (d) M = 1.03.
Figure 8.- Continued.
.2 [I'-- o Complete model I- .1 1] Lower vertical tail off "0 11h I- E o Both vertical tails off u ~ ~
""'"
0 ~ c: Q) ""~ (.)
~ ~
.... ~
""
....
-.1 Q) 't, 0 ~ (.)
~ 0- c:
- -.2
Q) ~ ~ E
'"
~ l"
~ -3 0' •
"-
c: ~ :c ~ .;!
-.4 '"
0::: ~
"
~
'"
-.5 ~ <;; -.6 ~ .60 ~ ,PV ~ Q) .56
'"
'0 .b~ II,
~ 12 or
-'<:
~ rL (.)
o .52 ?'
I, I
"c;::.
8:;
//11
~ .48 /"
II
~ -:7
I, I
.44
d 16/1
o
~ '/
~ .40 {7 'l¢
I)
~
1/1
.36
r/J
I
!J /
8.32
1/
i
Ii / ~ .28
11/
~ I go .24
II If
o
/ .20 Ij
V'
rU /
.16 /rY
/ V W
.12
V '/ /
j"~ "-.. .-0' V [ ~ / .08 OY' I"' .......
tL
h' '- .04 o .2 A .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, CL (e) M = l.18.
Figure 8.- Concluded.
.1 0 r-- Brakes r--,
o -
O Both closed Iv--.
r0- Lower open E - u I'--- In c- -.1 0- r-- -;: .S!
N ~ .!.!
P-- I'-- ~ -.2 "Ii"-..
'"
" "-..., i'--
i -.3
u~ "" E ~ , C> :§ -.4 , ~
~ "" '"
-.5
""
-.6 ~ /, '" 56
~ r
/
t:?
V
L- ~ 12 V- ~ ri I.
tf
,// 1/
.l2 8 o
'/
V V-
v:: v
/
.// /1
V V
:1
o Cl V- V I 36~
vv
l
ffi -4 ~ :~ '{ 32 ~ j C> II 28 ~ / 'fl 'j
/
/ / / / / p
r:L
/ V IrY o -,4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 Lift coefficient,C for C and a ,-, -----'-, ----'-, _---l' __ L-_-'--_-'---_--'-_---L-_-"-_-L_--'- L m -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for Co L (a) M = 0.60.
Figure 9.- Longitudinal characteristics of model with speed brakes open and closed; other surfaces undeflected.
13 = 0°.
.1
I ill
Brakes p- I-r---,:
o o Bath closed r-
c, I~ I'c Lower open I--
. "-:::--.-
<:> Both open E _ I Cl •
N
~ ID- r-- ,,~ [::II'- ~ -2 § .
"'Lf'-..
"1\
'-.
~ ~ -.3
E I"\'
g
~ I'\'
b. -,4
""
c: l}l, ~ :;:: !2 1"1'-
I"
a:: -.5 ~ ~ "'.
~ -.6 .6 8
""
!> 10 7 .6 4
I
I
.6 o
I'p
II I 2 0 .5 6 F V
IL I
~ /"
~ /:: 1
6 .5
.r:;:; . 2
v::
1 J
1;2
V- I
II
.4 8 V
/11
L0: j b{
c:?: ./'
8 .4 4 V I ~~ / ~lt:"
k-'" III
.4 V II
I
/L 1
0 .3 ,/ ~
I 1
V ,<;P' ~
/
4 .3
I JII
II
II
.2 8
I
V
/
.2
'l
L
IL II
/ / j J Q.
wi-"'" / .1 6
L
l,...E .1 2 It.;...
F
V
/
os
), o -,4 14 1.6 ID 1 2 - 2 0 .2 .4 .6 .S'----1 _---L • _--:-_---l:-_-::-_-;;-.-_-:;, :;---7;:' .-,':1'~'~I'
• Lift coefficient,C L for Cm and '!,.4 .. ::'.2 0 .2 .4 .6 .8 ID 1.2 1.4 1.6 1.8
Uft coefficient,C for Co L (b) M = 0.90.
Figure 9.- Continued.
.1
I I J J 1
t-.
Brakes
r--
r--c o o Both closed r- b: o Lower open l- i"'-- I 'CQ ~ r-r Jl--t-R.
D
E -.2 q ---c f'-- I'" ]j
IQ
L::-:: '0 -.3
~ I"-
]j -.4
'" 'r
§ E
1"'-
0. -.5 .5 i"-
..c:: I'"
. .g [J; 0.. -,6
I"'" 68
"- "- -.7
lJ·
I
-.8 60
III
/
I
~
I II
~ I?"
./.
~ ~ I
7'
/- I II
v.:
.....-:: ~ I 6
II II lL .~ o t) V V / 36 ~-
/' II
IL lL
0 ""
~ ./ Q)
V
32 8
.L 11
""
~
V
28 0
I /
It
/
II
V -.L / / ;:V y{ ::J.--.
-fa' .L ./
f'.. V
J
o 1.6 1.8 -.4 -.2 0 .2 .4 .6 .8L_-:I~:---0~1;:-2_-:I;::-4_~,;---;::--~,:----;,:,;:;-~,;;-o':' ;;--;-,;;' ,--;,'
Lift coefficient,CLforCmCl1d~4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8
Lift coeff icient ,CL for CD (c) M = 0.95.
Figure 9.- Continued.
.1 l I- BrOkes
-- r---,.c
-
I- o o Both closed ""- >--...
I--< -.'0. I'-c 0 Lower open I-- '""< <> Both open f'.... ~ -.1 "-.
[- .::::-- I--- E P--
R
'-' -= ~. -.2 ~ ~ ·u
"
i"--- ~ ~ -3 o .
u ~ ~ 1: ~
.""" 76
~ -,4
'" ~
""'n
E
, Y 1\..
"
.~ -.5 72 / ""-.
~ 't
_l
-.6 68 )
/ II b
I
l""- -.7 1/
I I
I /
I
II
I
20 56 /"
~ I I
v: 1> 1/
~ /'
~ I I
g- el. /"
j I
I~ ~ ". 12 ~ .",
u ~ 1:/ I II
g ,.....- ~
I r!
-5 8
V- I I
~ JlI o :;....- / II
/': I
~ 4 40~ /~ V" It> ~ ·0
./ /' / J /
36~ o )" r' '/ ~
.d. /' I / L
32 e
-4 o / l(
I c
II
V
I / / II
V
b /
t--- Ii>--
/ I
/ l-D
l.d
"-
IV
/
V
fa-- o -,4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 , , I I I L1 Lift coefficient,CLfor Cmonda_.4 --'---':--~-L--:---:'---:"-I~O=---'Ic':~2'----:-I.'-:14--:'I:-=-6---:'1'.8 -.2 0 .2 ,4 .6 .8 Lift coefficient ,C L for CD (d) M = 1.03.
Figure 9.- Continued.
I 1",-
I I I I
"- Brakes r---.-.
<> o 0
Both closed r-
I'-- 1o.l'o 0 Lower open I- '< <> Both open t'---P:-- J -.1 .....
~~ r---.-.
.~ r---.-.
~o..
.g -.2 p..:~ '1i; i'L ~
C -.3 """
Q) ~ I'Y E o
f'-- ~
~-4 '" .
c: ~ :c I'-. ~ ~ -.5 I'
he
'C -.6 68 lD -.7 j
If
'f ~ j /11 --"~ j
~ ~ U
'j ~ ~.
/. dlj
/
II
~ l/"
~ I /
II
-0 ~ / d
4 o t?' II <.)
p 40 _' c: j ..d~ I I .!!!
o u
l/ '1 II
36 ~ ~.
I 8
"'~
IV' c>
I /
32 .5
II
II
J 7 I
p V /
I
V
r7
~ ¢ P V / / V J-.....
Icr' / / V ,,/ t---.
-.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 -.4 , I I I I I I I I I Lift coefficient, CL for C and a_.~ m .6 .8 1.0 1.2 1.4 1.6 1.8 -.2 0 .2 .4 Lift coefficient ,C for CD L (e) M = 1.18.
Figure 9.- Concluded.
.4 -c
r-- \ Brakes
- .3 vI'--- o Closed o - Open E L p- o
ru-
~ •. 2
"'"
I'--- '0 ~
I '"
]
"" \"
'-\ " '\.
, "- .1: _
'" I
.c • '\. 0 ~ -\, -.2 "- p "-
'"
-.3 '" '7 /.,
:/
I 6 ~ ~ .60
/
I /1""' l'I .56 II ,/
V
I .52 / / .,4?
.4B
d' I I
o II
l:?' I
.44 '/ ~
J /
.40
'"'
I /
.36 Cl
/
o
II
i .32
u !
:?
~ 8 .28
/ I
'" e 0.24
V I
E
/
.20 ........ V
"--.... !'
~ .16 1/
/
.12
~ V
""-.
/" .08 -v .04
o
-.6 -.4 -.2 o .2 .4 .6 .8 1.0 1.2 1.4 1.6 1,8 Lift coefficient ,CL (a) M= 0.90.
Figure 10.- Longitudinal characteristics of model with speed brakes open and closed. ~ = 0 ; Be = _10 ; other surfaces undeflected.
.4 r-- '--( Brakes - .3 v- o Closed i'-, E - 0 Open ot-- U.
"~ iJ- 1::
.2 -
Q) ~r---.Iu "'-...
'u 0- 1""'-- ~ ,I 'n
1:: "-
Q) E "- ~ r-....
""
""-
0> "'-...
~ -I u • • '!= ~ a.
h'"
'"
-.2 ~'"
'"
~
"
,,~ -.3 B
V IJl--
.64 /' /.~
V
~ I
.60 \') ~ V I .56 /
I
V""
V /
.52 ~ II ..#
/
~ II I
AS V
.u
I
o II
-7 I
.44 V I ~
/
AO
II
D
~ /
<:= .. 36 c II
II
.!!!
u / / ~.32 0 I (,) 0> V I ~.2S II
l-P
/' 0['-.,
/
.24 ""'-- f.r.L ~ / .20
1/
d .16 ~ / 1"-.... V .12 p .OS .04 ~6 -,4 -,2 o .2 .4 .6 .S 1.0 1.2 IA 1.6 I.S Uft coefficient ,C L (b) M = 1.03.
Figure 10.- Continued.
.4 Or---..
Brakes - .3 Closed I", E f'o.- - D Open ..........
...: 1"--" I'---
°
c: .2 Q) u....
'(3 "b...
:;:: 'OJ
"l:J
.1 u 1'0.
"'"
"'"
1'0
"'"
"-
I'D: ~
"~ ~ -.2 f0..
,,~
'"
-.3
"'
drf
II -/ .60 ~ / LZ
/ I
.56 .//
-/ I I
.52 b?
~ II
~ .48 p-
~ I" I
~ .44 o 7"
..0 / I
II
0- /
-4 ~ 040
/
o
r
0 •• 36 pi / ~ '(3 j ii: .32
/ /
I ~ .28 V o
/
/ ( .24 ........
"....-V /
r---..
--,., / .20 V .16 ,P ~ ,,/ .12 -0' Y>.
.08 .04 o .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient ,CL (c) M = 1.18.
Figure 10.- Concluded.
·3 'J-...
1=
10 I"--
.2 8 .deg Brakes
e r-
"-- '0. 0 Closed
r-
°
E ~ 0-10 Closed 0, .1 ~ Q) lJ....
Ti ~
~ -
0-
ro. 1"0
~ Q)
r---.-""
-,I E
'"
I'-...
~
'"
0>
'"
1'\
~ -.2 .'!:
'"
a..
"- -.3
""
f", -,4 ~ -.5 V""' V'" L L
V V
....0.
V' V" 0>
Q) II
"0 ",' ./ ./ 12 .>o!' 48 V
V
I
~ V
~ lL
'0
./' 1/
lL
..9l 0> V
V
I
~
.,..,v
./V"'
JJL
Cl
l/ 1/ II
36°,
V V
J j V .S!
V
1 II
-4 32 ::: 1/ ~ 0> J,
/
28~
lLJL
,
L I
p
.J /
V
/
1/ ./
1;1 r:1 / !"
0- rcr- ""'" ..E o .8 \.2 -.6 -.4 -.2 0 .2 .4 .6 1.0 1.4 I I I I I I I I I I Lift coefficient ,C for em and ~. 6~1 "---~-~-~-~----7--;;--;;--7;::--7;::--7-:;;----;-'-1 :6;:;-----;-'1 ~8 L -.2 0 .2 .4 .6 .8 1.0 1.2 •. -.4 1.4 Lift coefficient. C for CD L (a) M = 0.60.
Figure 11.- Longitudinal qharacteristics of model with various oe and with speed brakes open and closed.
. ~ = 0 ; 8 = 0°; 8 = -7·5°.
a v .4 ILl" t-- 8 ,deg Brakes
r--c .f---- e
I-- .3 0 Closed
"" I'tr---
0-10 Closed I-- -.
"-- p- 0-10 Open f-D I-- .2 L!, 0 Open !'
~ f"-..
E I
° '"
~. ~ 10- f>,., l-
;g 0
'Ii; = f""::: ~ I ~'t ~o..
~~ "\ ~ f>,., I~ J
I
~ -.4
r7
~ ~ -.5 ~
~ fI I
[1 -.6
I
~ ~
V' I
I/- 'I
}II
L/
...:::1::/ ./ rl
p
V
V 114 I
~
V /./ I /
.44
il
P'~ /"
I
l/
Cl
:1
I
./ l/
40 o.
V c ¢ /.[;:7
17 (1)
'u II
,/ II
~ 36 ~ P' ~r'
II II
-fi 8
II ~
E7
k:? ./
'"
o 32 ~
/ j/
/11
b?'
Y /" -.t!/~ / r-I,p -4
I I r7 7
(.
lIV
II I
/ y V V '<>--. /
y I
~
"'" k /
I 1.6
l/
~ /
"'"
1"-1:.
.-/ /' ).../ 1""'- If.).- I--- , ,6 -,6 -,4 -.2 0 .8 1.0 1.2 1.4 1.6 .2 .4 I I I I I I I I I I I I Lift coefficient ,C for C and a t m L 1.2 1.6 1.8 -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.4 Lift coefficient ,C for CD L (b) M = 0.90.
Figure 11,- Continued.
.4 ---c Il ,deg Brakes t'----ri e I- .3 0 0 Closed '--[ 0-10 Closed I- .2
"'"
I'n
J .1
"E"
""
J-
l-- 't
'"
:~ 0 1;; 10- "- ----- 'b-, "- ~ -.1 ~
"""
~
I'..
b,-.2 c i"-,
1"'-
:e }2 a:: -.3 f".
'"
1'\ -,4
T
""-
II
-.5 i",
I'D I
-.6
i'J
I
)/<:J V V V
1ll
V'"' V
II
V lL 1
V V L
1 L
V V II
,....., fA-'
V V
V
/v
V 2 lL
V V V /
l/ L
o /V' V
V II
l/ -/ I 1
-4
II JL
I /
V V
L
IV
/" ;f
I"- V
~ /' ,....-
"-c V
I~ /c< ~
o
-.6 -,4 -.2 0 .2 ,4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient ,C for Cmond ':...6:'-' _--,:-1 _~'_~I_----:-_---,:'_---='----='--:-"::---:-":::------;-,--:-----:-,'':::--~ L -,4 -.2 0 .2 ,4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for CD L (c) M = 0.95.
Figure 11.- Continued.
,4 8 ,deg 10- Brakes i- e t--- I-- .3 O 0 Closed r0- 1---- D -10 Closed I-- r"-- o -10 Open 0- I-- .2 L\ 0 Open r-----k> ~ 1"'--- 1'1:: I
J
"- ~ -E
p-
.~ I"::-
"
o
""
1- r--,
lOt---
r--
]
"'~
'"2!R
ll"- l"- C _.1 ~ If ~
~ f:0
'"
o ""'-
E II
~ ~ &> -.2 ~ "-~ c 1: 68 .B I ()I ~ "10..
0:: -.3 '( VI (.
/'b
III
I
1\.
-,4
17 J
t II
IQ -.5
II I
I
I\..
~
r7 1
-.6 '\
T 7
III
20 A/ . / I 1:9"
1/ V 7 .~
V /V
7 1711
~ fY"
V
l/: I V ~
/ V ~ './ p-
k;:: I]
..-<=f?" II
::/ I
II
V .4-
];7
7 7
V ~
/ k;::::V' //" /
~~ / / I I
/ ./ ./ o ":{ /'
/ !
V
/"'v ~ 7
?'
In;:::: J.L 1-' -4 v~ /
/ / /"
if IZ'I:::- n..
/ /
V
'd
V
V
I"""
1'--b...
tr
P---t---
V
'" .08 .6 .8 1.0 1.2 1.4 1.6 -.6 -,4 -.2 0 .2 .4 I I I I I I I I I I I I Lift coefficient, C for C and a ' L m .6 .8 1.2 1.4 1.6 1.8 -.6 -,4 -.2 0 .2 .4 1.0 lift coefficient,CLfor CD (d) M = 1.03.
Figure 11.- Continued.
.4 01--- 8 ,deg Brakes e .3 r- 0 0 Closed
h 'rn-
0-10 r- Closed '1: "---- \'-y r----- 0-10 Open .2 r- 6.
ru- 0 Open
'~ '<;) r-----
~ ru
'" llr----
."'-
I'----
"<
r-----
~ to- ~
I'( ~j).
~
""
~ ~
'"
~a.
~ ~ ~E;::."
~ '\~
f::0
-.3 't ~
/
I~ I -.4 '\ ~
,"'- 1
-.5
to
W
I
1 1
V 1.0 I
'1
V
~ ~ II II
F' .LV'"
IL lL 1
t
V-
V / /
.=;- 12 44 I""" u /1/"'
k" l~
,g o V ~~ J '0 8 408
.# ~ ~ Lt 1
~- j::/"
""'"
V .,c:.
V 11/
f
4 36~ I"'" 1.# ~
! II
j:?
~ ..0 III
o 32 ~ j:7
lLV Cl
I~ h? II
k:;:: 1:7'
/ 1.1 Ii
-4 28 II j / 10.
L 1~
. 24
1"- -"v ../
rv
"'r---: .4V IL lL
/ / P .d _I:: V L /
V
I'--
10... /11'
I"" -.2 0 .2 .6 .8 1.0 1.2 1.4 1.6 -.6 -.4 .4 I I I I I I I I I I I I Lift coefficient ,C for C and a ' L m -.6 -.2 .6 .8 1.0 1.2 -.4 0 .2 .4 1.4 1.6 1.8 Lift coefficient ,C for Co L (e) M = 1.18.
Figure 11.- Concluded.
.3 1'0- ]V f--", Brakes e-- 8 ,deg .2 e 0 Closed
r--- 0
I-- -T'--- ¢ -10 Closed I E (.)
b 5;' 0t-- f'--.
·u 0 P- ro ~
~
1'---
k.
~'"
I I'---.
['y
"<
'"
/',.
lO, ~ l'" -.4 7' /p V ./ V / V
V
V I
V V
II
./ V II I V V
.r<V II
-/
V 7
o
V 117
/ V
V
-4 ~ o
II
32 ~.
I .~ III
28 ~
u I g' II II - II 2) p
/ /
.1 6 / / lP /.< .1 2
V
P-- ./
-.....
t-o. -v
""v
~t--. Jcy o -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 -.6 L1 Lift coefficient, C for Cmand« _,6 -_-,.L --_,-'-2----'-b--.--'2---'.4---'.SL-.-. LI --,1.L: -- .L: ----'-1 :4.,.---I.11. ----J I,8 L 8 0 1 2 6 I Lift coefficient ,C for CD L (a) M = 0.60.
Figure 12.- Longitudinal characteristics of model with various Be and with speed brakes open and closed.
~ = 0°; Ba = 20 ; Bv _= 0°, .3
1 l J J 1
Se,deg Brakes -<J 1"--0- .2 0 Closed I- ------h 0 0 Open I- 0-10 Closed
1"'-
.1 "'- E '\ jQ- ~, o c Q) '\ lor ;=:::
t9-
'<3 '--d '\
"" -.:::-
d; _.1 8 ......... ~ I"\.
1: ~
1"-
~ -.2
1"-
LS
~ 0> 1'(; k> i -.3 . .g I~ .6 0.. 8 I~ -,4 I~
I
.6 4 '-':t'-.., -.5 't: ~. j ~ .6 o
I
I
-.6 .5 6 ~/
// I 01
.5 2
1/
V /.::: ~ V;' V
1 I
1//
V ~ ~ 1
V- V /
I/
I
~ / ~.
I/, ~
~ 1
40 0 V o
,L 11/
~ -'" 1:' V
V I
I
36·~ F V ~
!/ .:1
~ o
V
/ I I
32 u II / 4 ~ o j
IL
II
I)'
1/
/
/ /
V V'" 10..
.0""
II
/
,X- I L
J"-.. V
~V I'" o -.6 -.4 14 1.6 -.2 0 .2 .4 .6 .8 1.0 1.2 , ! ! ! ! ! ! ! !
·Lift coefficient,C far em and a _. 6L.! ---'.4:----.-:!:2----=-O--:.2~~.4~~.6--.8~-7I.;.-O-,..I.:;-2 -1i':A;;:-'I.'e;:6~1.8 L Lift coefficient ,C for CD L (b) M '" 0.90.
Figure 12.- Continued.
·3 10-
- I'--
0- I I I I I
(le,deg Brakes ---P--.
.2 0 Closed I-- 1"--- <> -10 Closed I-- ""1'--,.
.1 f'.- f>--.
"-
E 0 ........
-0...
l"-
u.
1:: I,
I'
.!!!
I .~ J'.-...
~ 1'0...
f',.
'"
u -.2 "-
I
f".,
'"
b E -.3 , 0> .5 .c ~ -.4 1'0 1"-
If
-.5 '0
"""
-.6
/
~~/
V /'"
V 1// /' ~ V 'j /' V
1/ /
V
VI
V
V
lip
.-.-.v
Cl
V 1/ /
40 u.
,/ 'I 'E
./ .!!1 /'" /' ')
~ . 36 :E
Q)
/' 1/ III
0 8 V
V fI
32 ~ V Cl
H 11
./
rJ
1/
i /
V /
II
Y" x
V
/
J'.-... /' h. V
V
P--.
[:Y o 14 8 1.6 -.6 -.4 .2 0 .2 .4 .6L-_. 1,-' _--,I~.,o_-:!I.,~2_-;;-_~,;--~,:---~,_-,Jr' :;--f;:' ,~' L-II';;iJ ' Lift coefficient,CLforCmand~.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for Co L (c) M = 0.95.
Figure 12.- Continued.
.3 r--
~ I 1 I I I
8 .deg e Brakes
r---
.2 0 0 Closed r- 0 0 Open r-
""
o -10 Closed
D
.1
J
"-
P-j--. '"
~ 0 , ...
'0 ---b "-~ J0..
:E I"" "- b~ § -.1 1:: b.C'-- .76 E '\~ 1"82: ~ -.2
~ LL
go .72 "-
l3
~ -.3 IC!\:~ ti: / 'V .6
~ 't
LL
-,4 ~ .6 4 ~ -.5
g
j ~ [J;
//
-.6 .5 J.,
Irl
2 0 F""'.
1/
£ IL:: '1
,5 2 V ~ ?'
~ ~
1 1 L
.4 8 I
,. .... v
/"
i
V V ~ 111 .4 p-
-.<::: i
~ 1 Cl
u
L U
~
.4 oi
p- Q) /V
I...-" / 11/
Ti II :E V V /V"
i I I
!L /
C> o I V V
1/
id"
~ ~ L !
V II
!{ 2.8
V
/1
,..f:V V Ir.l.
2.4 .if "-
VlL
1/ ,/
V ~ / ~ ~ kY'V r" "r-.
J..---"IT r--..
-..:,
o
-.6 .2 0 .2 .6 .8 1.0 1.2 1.4 1.6 -.4 .4 I I I I I I I I I I I I or and a I -.6, -.4 -.2 .2 .4 .6 .8 1.0 104 o 1.2. 1.6 8 I.
Lift coefficient, C for Co L (d) M = 1.03.
Figure l2.- Continued.
. ..-----r--o<r-i>---rr--.--,-,---,-----r--,-,----r--,-,--,-lTi- I I I 1 1
Be ,<leg Brakes
LGl-i---+---=+ ~r---.,~ . .J---+--+-+++-+--1-t--Hrl---t-t-t-t-t"'11l 0 0 Closed !--
.2 ~ 0 0 Open!--
l-l-i---+-+-I----I--+~,+++-+-+-t--hH-t-t-t-tIIIIIIM <> -10 Closed
LLLW~~~~~4+++++++TTTTlllrrrrrM
E
.ILJ~~I~~'~~~+-~~~'~-+~+-~-r1-ti-t-rt-rt-t~t1-rilr-rTl
'-'
o.r---- ~
2 0 .4 8
'"
~'I 2
i
'.
~
v~~ / J
'0 .91 408 ~ i:: Q)
/' V 1/ /
36:§ :t: V /V'" II Q)
32 g
v
II
L/
U-l-J--1----W-I----t--l--t-+-I-+-i--H-+++-H?tft-H-tTiM-rTin·
U-kW-+--+-W--I-+-t-++-H-++H++-H-t--HIIHIIMI1·
-.6 -,4 -.2 0 .2 .6 .8 1.0 1.4 .4 .2 1.6 I I !
I I I I I I ! I I Lift coefficient ,C for C coo ~.6 L m -.4 -.2 0 .2 .6 .8 1.0 1.2 1.4 1.6 1.8 .4 Lift coefficient, C far Co L (e) M = 1.18.
Figure 12.- Concluded.
.4 {3,deg 8e ,deg .3 f- a 0 ~ l= cf -5.1 f-
NBr--. 0
o -10 .2 f- 0-10 -5.1 I'-- hE?
~ E .1 ,,~ u_ c: 1a'J, Q.)
J".."
'u f" - f~
lui
~
u f"--- b -.1
""
Q.) I
" i'--
E "~
') E -.2 , 0> ~ I>., -.3 0: '<OJ", f".- -.4 I"" -.5 (l'f / / "",V'
V
V V"
'" {!l
..:.
Id' V / -'" u .e V
I
V
V .v' M'" '5 8 ,....
I] ~ V V g' <:( V
/ I
"""V JP
'I IT
,/ W 3,6 l.C V /
/ II&-
]IT Cl V / u -4 ~
,,-
. / 28 .!!!
u
r 7
~ 24 8
/ /
'" e Cl ~
II
~
/ /
W
lJ" El"-
V
"'- V b--i= V '" '" t-- ~ -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 I I I I I I I I I I I I I Lift coefficient, C for C and a L m -.6 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 -.4 Lift coefficient,CLfor CD (a) M '" 0.60.
Figure 13.- Longitudinal characteristics of complete model at ~ = 0° and _5.1°. 5 = 0° and _10°; e other surfaces undeflected.
.4
h-- J J I I J
LE 8e ,deg {3,deg r---~
o r-
.3 0 0 :B I'----. cf 0 -5.1 l- f'.., o -10 o r- .2 c( -10 -5.1 ~ E ~ I 0.
"E ~ Q) OJ'- r-- ;-t"
;g 0
~'"
1"""- gs ~ ~ u c: i'--.
I ~ -.
"1 'r=~ o E l"- ~ -.2 e:--, c ~ ~ 0.. -.3 "- -.4
"
'e
P
~ -.5 ['), r
/
-.6 2 0 I/"
V 'PI
~ V II V V'
l
V V- IJ
.[1 /" V [I -" u g o
V L
'0 V V
If
V
V lL
...... V
I
.c' JW' f'"
V V !' lL
V ./
/ I
V /'
/
II
l /
1/ / /
r
/
)'
Fe V
V
"""'r- k"
-~
~ .tV
"r- 4 1.6 -.6 -.4 -.2 0 .2 .4 .6~_.8L-----II.~0_-11.2=----!:li:--~':----;'_~' _~I :;-~I ll'-;;;:-II'I~i'"
Lift coefficient ,CLforCmand~.6 -.4 _.~ ~ .2 A .6 .8 1.0" 1.2 104 1.6
Lift coefficient ,C for CD L (b) M = 0.90.
Figure l3.- Continued.
.4
I I 1.1 I
'"
8e ,deg /3,deg
Ii
-~ .3 - 0 0 0
N"
CJ' 0 -5.1 r-
I'---
o -10 .2 0' -10 -5.1 r- l'e::
E 1""-
l) .1 "- IJ- '"
r-
N J<!iA.
~ 0 b~ l'-.
) -.1 "- I"" i'0' L"-..
g' -.2 :c
I"'-
~ ~ tB' a. -.3 ~ I\.
-,4
!
"'"
IL
-.5 ]'" / ."...
-.6
'rl
.5 2
/
V' V 1// L
V
V ;1
V"
1/11
V ""
V iL /'
/' /4
,/
IL If
V
r ""
~ V 1
.,...,.V
/
1/ Irrf.
V V I"'" V-
k:: /1
/' v I
1/
L ~ / ..L
lL ~
Y
n
V
II
/ L / .
V
Jf
;= ~ / .
V J"...- "If 1.,.. JliJ,v' .c.
.08 i' 1",,1/ .04 o -.6 -,4 12 14 1.6 2
.2 0 . ,4 , .6!o-_.8=-~I.O;----;!::. _-;;.' _~li;-~'_~' -i'r1 .-Tl?'l4'lil ;:-1'
Liftcoefficient,CLforCmand~.6 -.4 -.2 b .2 .4 .6 .8 1.0 1.2 1.4 1.6. 1.8
Lift ceeffi ci ent ,C for Co L (c) M = 0.95.
Figure 13.- Continued.
.4 F" r---- ,8,deg
--. lle,deg
II-- .3 I-- 1"'- 0 0 ~.
(f -5.1 I--
",,--
0-10 .2 r-- 0-10 -5.1
"'-
lID E .1 Ll.
"-
I"- I--- ~ ~ ~ ~
~ 0
'ti1Y
",,--
l) _.1
'"
"-..,
1"'-
'"
I
"\ "- IT -.2 0> ~ c:: £ ~ b
'"
<l: -.3 I'"
@ ~
f
/
-.4 "'-
i"-.
PI
-.5 "-
fj
"- 56
il
-.6 (l1J
/
1// ~ I'" V
~ I
V ./
/"
I"-' ,/ /' II r:\y g /'
./ /i
d- 12
V /1/ ~. .v ,.v p'/ / ~
~ 8
i-"""' ,.v /'
/ /
'0 ./ .9.!
,/ V
.w 4
V V
/ /
r-
/ I? / /
o
,/ V
L p
...r l.? V /
-4 / /
V
/ /
/
n] f$ .1
~ / /
.......... .v
~ V
~ ~
V-
I--- I~ o -.6 -.4 -.2 0 .2 .6 .8 1.0 1.2 1.4 1.6 1.8 .4 ,.
, , , , , , , I I I I Uft coefficient ,CLfor C and a I m -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for Co L (d) M = 1.03.
Figure 13.- Continued.
.4
I I I I I
f3.deg .3 o f-- -5.1 I- o .2 -5.1 I- E .1 0_ I"", -- 1:: 1"-...
Q) :Q
~
u I
-
1:: Q) E E -.2 .
0> C :<: u -.3 if -,4 -,5 ,5 6 IY -.6
!
.5 2
I I
2 0
II
v
/'
I
il /v /"" 0> I~ ~_I 2 <t
I
-"" 40 u
v V
'I
g
~ rl
'0
I
'" 4
g> «
v
I
32 ~ V ./
I '13
tt: Q) / 28 8 1/ V
7#
'" e
/ 24°
/11
/ /
o
-,4 -.6 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 . ! ! I , ! , ! ! ! ! !
Lift coefficient,C for C and~.6 L m -.4 -.2 0 .2 .6 .8 1.0 1.2 1.4 1.6 1.8 .4 Lift coefficlent,C for CD L (e) M = 1.18.
Figure.13.- Concluded.
.1
o
.. e--- {3,CiBg I-- -VI ~ o 0 ~ I
-
o -5.1 ~ ~ '\ <:l\ '" ~
'\
g
~
~ III
'(/ ~ -.5
~ fl
IL
-.6 '/
h
!""' ~
Iii
pr .~ .#
V
JL
~~
III
# l .
a
~ II
u -:?
/I h )
k?
~ ,-6
fJ
\ ~/ / ,.....
o
-7 II
.
~ ~ / -4 /
J
/ d a
!-P'
rn '-- .1 .1 2 -.6 -,4 -.2 .2 .6 .8 1.2 1.6
o .4 1.0 1.4
I I I I I I I I I I I I I lift coefficient ,C for C and a m l -.6 -.4 -.2 0 .6 .8 .2 .4 1.0 1.2 104 1.6 1.8 Lift coefficient ,C for CD l (a) M = 0.90.
Figure 14.- Longitudinal characteristics of complete model with speed brakes open; other surfaces undeflected. ~ = 0° and -5.1°.
.1
I I
_r.1
I I
o
(
to-
l:r.r:J (3,deg E .7 6 <.)
~ 0 0
P----
t;" -.1 o -5.1
"I"-- Fit'
.~ .7 2 f'U
.L
~ -2
u '.
"'r--.,
'I
E Q)
jII
~ § -.3 E
~ /J
.6 4
II I
~
r -4
u ~ .
II Q
0:: .6 o
l"- I
-.5
1//
~ .5 6 r~
P
-.6
¢I
.5 2 II 'I ~ V b- II ~.
IlL 44 a ~ V <.)
~ I t[ 12 E" U ~
llJ
Q 40.~
rp
<;:: V .L- ~ 8 jP-' 'tii ·0 o
~ II
~ 36 u 0> V
~ V
.[4
~ ~
l2
~
1..0 /'1
bfo'
t2:
V
bt; I~ ~ tk .~ r--.., 1.0;; P' -.6 -.4 -.2. 0 .2. .4 .6 .8 1.0 1.2. 1.4 1.6 I I I I L- __ ~I __ ~I~~I~~I~~I~~I __ ~I __ ~I __ ~~~ __ ~~!
Uftcoefficient,CLfor Cmonda -.6 -.4 -.2 0 .2 .4 .6 .8 10
1.2 1.4 1.6 1.8 Lift coefficient. CL for CD (b) M = 1.03.
Figure 14.- Continued.
.1
I I
B~ I I
o ""'Ibn.
deg .8, l- E (.)
o 0 '<i:r-----.
~ -.1 0-5.1 -
f0---
'u i: t"-.
8 -.2
P--
1: .6 8 Q)
§ -.3 ""~
, ~ ~ .6 4 CI /
i! -4
.l:1 . "
/
0..
a::: .6 o
""
-.5
fa 1
'"
.5 6
/
-.6
£
/
/
1£
V
V- I
V / I
V-
40 Cl .,."V IJ (.).
c:
V-
36:§
V
I
~
""'"
V
32 ~ /"
II E!
Cl I>"
/' -.I
~
""V
=
V
V
/~ \W -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 I I I I I I I I I I I I I Lift coefficient, CL for C and a m -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for Co L (c) M == 1.18.
Figure 14.- Concluded.
.1 Id.f--..
v
J 0
SJ)::::: :% co - .B,deg
-"
OJ ~ o 0 a
;g -.1 -
0-5.1 '1i; ~ ~ C -.2 OJ ~ E o ~~ ~ -.3 u: g' ~ :.c u ~
i5: -,4
r'O
-.5 _& ~ )k!
/'
V /
,,>,,,""
/
L
V
/ .,/"" ./
V
J
o I~ 32°.
"" C
,/ .!!1
o
u /'
/
28:::
..,..v
I
-4 ~ 0> 24t5
II
~ /,
"
Iff
,/;
/f'if
r'
/' 9- ~ f-'" ~--- [Y [:Ii ~ -.2 .6 .8 1.2 -.6 -.4 0 .2 .4 1.0 1.4 I I I I I I I I I I I I Lift coefflcient,CLfor Cmond a 1.4 1.6 -.6 -,4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.8 lift coefficient ,CL for CD (a) M = 0.60.
Figure 15.- Longitudinal characteristics of complete model at ~ = 0° and _5.1°. ov=-7.50; other surfaces undef1ected.
-~ -,4 ~2 0 2 .4 .6 .8 1.0 1.2 1.4 1.6 I I I I I I I I I I I I I Liit coefficient ,Cl for C and a m -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8 Lift coefficient, C for Co l (b) M = 0.90.
Figure 15.- Continued.
\ \ j::: t-- ::--E
I I
J 0
ieJ:: ~
.B,deg I-- 1i --.::: ~ .~ -.1 I-- o -5.1 "':i"!a,
]
~ 1= -.2 ~
"-
o ~ ~ - 3 0> • C
:e "'- .6
~ '\.
a:: -.4
.6 o
~~
IlL
-.5 .5 6 ~
b
-.6 .5 2 ff V'" Ii
II
V-
V' 0>
VI
Q) ".
J.
,k" <:S. 12 ->< 1/ u Jt.
"'"
~ If
V
'0 8 Cl ,/' ~ .l!! 36 L).
V 'E
./ III
.lI!
~ 4
u
V
32~
II
L 8 o 0> V II ) ,/ -4 ~ j
!L
;1 V f.it
'P
,.1
@.....
/.b::/
V
...... - I.!Y'
o
-.6 -;4 -.2 0 .2 .4 .6 .8 1.0 1.2 1.4 1.6 I I I I I I I I I I I I I Lift coefficient, CL for Cm and a -.6 -,4 -.2 0 .2 .4 .6 .8 1.0 L2 1.4 IE IS Lift coefficient, CL for CD (c) M = 0.95.
Figure 15.- Continued.
.1
I I
p-
t-
Nt--- I I
o
"(5 ~ ,B,deg - o 0 ~ts:, -I l- E • n -5.1 ~f.r., 0.
1'CI::::s::" ~ -2 :Q .
"~
~
~ u -.3 .~ .6 8
~
~ ~ -.4 , ~ 0> ~ .6 4 c:: ti~ {3 - 5 if .
II
" .6
o VI
"
-.6 't /, .5
J1
-.7
VI
.5 2 J
~ II
c::./
I{L
V
j
V
JL
Y f/ L o
V
iL
°
V III
36 ~ Ti k::: 4 tt: Q) V
!
0>
k::: VI
E V o
A
(j /'
;1
~
ld
r!- ~ rz: L~ V I:S;;: ~ --.. ..
.r- f-L'Y .04 Q -.6 -.4 -.2 0 .2 .4 1.2 1.4 1.6
Lift coefficient, C for C ord a .6. ---.8~--'~D--~--~I--~I---z,---tI--~I~-tI~-tI~IU';--rI
L m !:-- I I I . 12 14 16 18 -.6 -.4 -.2 0 .2 .4 .6 .8 1.0 . . . .
Lift coefficient, C for CD L (d) M = 1.03.
Figure.15.- Continued.
.1 R.
1 1
r-----,
1 1
o
(3,deg h9- I-- E 0 "~ 0._.1 I-- 0-5.1 1:: .!!1 u 'Ig,
'"
~ -.2 1"'- 1:: ~ -.3 o I"
"'"
E
g -.4
:c
tr0
.l2
.6 o
j a:: -.5 ~ 10,
si
.5 1/ -.6 j .5 2
/I
ld III
rI V ,>'"' /, ./
~
V rjj ..:. 12 F u
V
E o ~V
/I
'0 8 Cl
V III
36°.
1:: j, ./ Q) 'u
V
I II
32::: VI ~ u L
o
0> /'
J/
28~ V ~
JL
fj
ld
~
W
11-
~
IQ- /V
-.........: :.6-1-"'" H': .04
o
14 .6 -.6 -,4 ~2 0 .2 .4 .6 .8 1.0 1.2 ! I I I 1 I I 1 L1 Lift coefficient ,C for Cm and a _.6 -_-,41:- ---.2~1 _-O!:-I --.~2--.4';---.~6--.*8--7;1.0;----7.1.2;-~1.4'-1~.6:J'1.8 L Lift coefficient, CL for Co (e) M = 1.18.
Figure 15.- Concluded.
,,'O~II f III HI III t 111+111 t II H II
-.01 .04 I t- t--.
~
F::: I::::::-
.03
F8
----
8 ,deg 8 ,deg Brakes e v n C .02 0 0 0 Closed 0 0 -7.5 Closed <> -10 -7.5 Closed -7.5 Open '" -10 .01 D 0 -7.5 Open .05
r-
I-- ,04 t-
r-
t--=
t-;:,
f::::: ~ ~
.~
r--n
~ .03 ,;;
'"
en .02 ,01 o ---.,
---
-.01 ~ _':1 r---r-------r-- I i I r----r--r------ llllr----r--r------lll r----r-----r---IIT I ~II J I r---r---r----r-II j i r--r--r----r--11 Hill
l
'-6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ottock,a,deg (a) M = 0.60 and 0.90.
Figure 16.- Lateral-directional characteristics of complete model with various Be and By and with speed brakes open and closed. ~ = 0°; 5 = 00.
a
<~111111 tuUlfH1fttHHft II
.05 h- ::--:--..
.04 r-::::: i::::--..
~ ~ .03 '<:) C n 8e ,deg 8 ,deg Brakes v .02 0 0 0 Closed 0 -7.5 Closed <> -10 -7.5 Closed .01 b. -10 -7.5 Open D 0 -7.5 Open o
- t---<
C, J 11111 HHJ IIITll11111 J 111~111
c,_] I ~ III mH III ~ III HmHt11 i
.05 ~
.04 =-
"'" ~ V
'""'8'" .03 C n .02 ,01 o C, _ ~Ir---r-----r---- I i I r-------r------II Httir-------r--r---II------r--r----TIT I i~1i I :~I J I :---,---,---;--rI:fH '-6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ottock,a,deg (b) M = 0.95 and 1.03.
. Figure 16.- Continued, CI] I! 111.111 ~ III{ IIIH IH I: .06 I--'
.- r--
.05
---
-
-
-<"> -(; .04 .03 8 ,deg 8 ,deg Brakes e v C 0 0 n 0 Closed 0 -7.5 Closed .02 <> -10 -7.5 Closed 6-10 -7.5 Open D 0 -7.5 Open .01 o -.01
C, J I{ 11111 ill I I I""}' 1111111 J II E II
~6 -4 - 2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ottack,a,deg (c) M = 1.18.
Figure 16.- Concluded.
.01 ..,.
j:;:::: =:::::::: b-::: H r::=:=- --<:. :::::::- :---c;
.r-- ~
H<
o
---<;
- p--
-
c -.0 I .03
V"
.,/ ...0
/ /
.02 ./
Y
A.
~
/
.01 ~ ~ v
V ~
o
v
V
~ ~ /
I--' -[I-"""""
--
/
-.0 I
- ---
--
V
V
/-
-.02
/
-/ 8e ,deg 8v ,deg Brakes
/
-.03 0 0 Closed
V
0 0 -7.5 Closed /' 0-10 -7.5 Closed
V
-.04
. ---
.r---
--
-
-.05 .2 y C .1 "\:.
..
v M=0.60
-4 -2 o 2 4 6 8 10 12 14 16 18 20 22
Angle of attack ,a ,deg (a) M = 0.60.
Figure 17.- Lateral-directional characteristics of complete model with various De and Dv and with speed brakes open and closed. ~ = -5.1°; Sa = 0°.
.02 --::>,
---
_0--
--- ~
.01 ::---
---
r:-----
~ ~
"'-
----
C z
----- ~
r-::::::: ~
-<I :8 ~
;:::=: F-:::
;3. ~
.-
~
~
~ h---
~ ---
~
<~
-.0 I .05
L
.04
V
/
L
V
""V
.03 r- t----
V
Arr-
./ --.:
----
Llf
.02 r-'"
V
V
L ~ ~
V / ~
~ .0 I
V
V / /
V
V
/ .-/
C n 0
V
L ~
t?"
~ ~ L'-
-.01 I-- t------, .~
LV
V
/
-.02
V
V
L -.03
V
V /J: Brakes 8 ,deg 8v ,deg e -.04 0 0 0 Closed
V
0 -7.5 Closed V <> -10 -7.5 Closed ~.V [; -10 -7.5 -.05 Open f.-- D 0 - 7.5 Open "....--
---
-.06 .2 ~
r-
'"
C
y .1 =---
'"
~ M=0.90 ~ I ~6
-4 -2 o 2 4 6 8 10 12 14 16 18 20 22
Angle of attock ,a,deg (b) M = 0.90.
Figure 17.- Continued.
.02 ~ ......"", ~ ~ ~
-
b?'
-v r-----:::
"1'8
/
.01 ------- --::::::
--X ~ b:l
C 'J
-----
1 r-- D-- ~ ~ ~ r-- A .-l;J--:: f.--C I-----"
-
---
-
~t)-- -.01 .03 .A8 ~
/
.02
/
V
.01
/"
f"
/
--:;§.
~
i="""
P
-.01 po-
-d --
/ en / / -.02
V
rV
-.03
/
/
8e ,deg 8v ,deg Brakes -,04 0 0 Closed
V
/" 0 -7,5 0 Closed .-A.
() -10 -7.5 Closed -.05 ~
---
----<
--
--(: ---
.D- .~ -.06 ,2 I--
-
-0 C y ,I y
'"
M=0.95 4 6 8 10 12 14 16 18 20 22
-4 -2 o 2
Angle of attack,a,deg (c) M = 0.95.
Figure 17.- Continued.
.02 ....- --r--..
r--: p;;;
Vfr
t---,.
/ .01 H ;p,
I~ k
Cl
V-- r-
!>?:
~
~
-=
~ -- ::-:
-
j<;:---- -.01 .05 71:
'/
/
.04 1/ /
1/ II
.03
:/
/ f1l
A/
V
/
.02 P- ~ ~ ~~ V'
I:?'
./ h
.0)
? ~
h, ./
j;/v
v
.~ k: C n 0
v
?'
/- l:::::=
V V .do ~
.~ ----
I-- -.0 I ~ .~ r:=--< -, ~ / -.02
V
[7
-.03
/
V
./ 8 ,deg 8e,deg Brakes v -.04
0 a a Closed
V
a -7.5
Closed
__ v
v 0-10 -7.5 Closed -7.5 -.05 Open '" -10 D
a 7.5 Open
-
-.06 ;2 t--
-
k
C y .1 "" t-- M=1.03
-
N
14 16 18 20 22
-4 -2 o 2 4 6 8 10 12
Angle of attock ,a,deg (d) M = 1.03.
Figure 17.- Continued.
.01 H I---: .<'0
--
,-
Cl t;:
~
-
-.0 I .06
lL
.05
/
/ .04
V
~
V
./ ~ 0
.03 ~.
~
L
-" ..cJ
V V
./ ~ .02 V
/
~ ~
V
/ ./' '/
.01 /'"
.v >.~
~.
1/
/ en
v
1/ ~
~
V ...,,~
-.01 ~
~~
v .po
-'r-
ID -.02
V
V L -.03
V
/""v -.04
)V
- V Ile,deg Ilv,deg Brakes ./' -.05 0 0 Closed V 0 -7.5 ,../ Closed <> -10 -7.5 Closed ....(1,.--
-
to. -10 -7.5 Open -.06
-
D 0 -75 Open -.07
~] 1llllglllMllllllll~mlll
-6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of attack,a,deg (e) M = 1.18.
Figure 17.- Concluded.
'1_] I HfH 1.1] II Iff IIH II
.01 o ): IL' -.01 ,/ ..-L /' /' -.03
Y ,B,deg
V 0 0 ,-/ -.04 o -5.1 I--
-
-.05 .2 .1 o ~ M=0.60 -.1 .01 o r-- -...., -.01 -.02 LV /' L -.04 V V -.05 f--
--
-.06 .2 .1 o M=O.90 -~6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of at1ack,a,deg (a) M = 0.60 and 0.90.
Figure 18.- Lateral-directional characteristics of complete model with surfaces undeflected.
~ = 0° and -5.1°.
o --.
)J -.01 -.02 V V
v
/ -.04 V {3,deg --' 0 0 V -.05 o -5.1 --" V f-< -.06 .2 '---<:
-
.1 Cy o M=0.95 -.1
c, .O~II tOOl J#II [fIll t 1:f4ttfM II
-.0 I o -.01 J / / LV -.04 ./ V /' -.05 .2 -""'1: .1 Cy o M=I.03 -·.!.6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ollock,a,deg (b) M = 0.95 and 1.03.
Figure 18.- Continued.
.01 L U I--
-
f.---f-
C1 -
J -.:.
-.0 I .01 '- J -.01 -.02
V
C
n ,/ /' -.03
V
/' /' -.04
[V
/' ,/ -.05
V
,.........
,B,deg ~ I-- ..rl!-- -.06 o -5.1 l -.07
.2
'U .1
C
y
o
M=I.IS
-2 o 2 4 6 S 10 12 14 16 IS 20 22
Angle of attack,a,deg (c) M = lo18.
Figure 18.- Concluded.
'I·O~II um 1+Hf1t11111111 thFFII •
. 02 ,B,deg c 1/ 0-5.\ .01 // / 1/ V -.0 I
V
V V -.02 -+-
c, ~ottf III rrm II UJ 1111111 II H II
I.---- ../
--
.01 V V (.-0 ~ y- Cz 0
--- -u
L----' ~
-
-.01 .02
r
/
.01
/
1/
i--...
/' --0
V -.01 /1/'
V
-.02 V I-- J...- t--f-
--
-.03 .1 M=0.90 -c!.6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ottock,a,deg (a) M = 0.60 and 0.90.
Figure 19.- Lateral-directional characteristics of model without lower vertical tail and with other surfaces undeflected. ~ = 00 and -5.10.
(3,deg ~1--
.02 f------+---I--+--+-I--+-+--I--t--I--+---+---io 0 / r--c ____ k
o -5.1 ~,~
/ --r--c
Cz .0 I f-----l--I---I-+-l-+--+-+-+----+-++-+--l-l7Lf---+-+--t--+-+-+-t-l--+--+-t-----i ./ .02 J V .01
V
l(
o ~ V
V
-.01
/
// -.02 .... )/.1
Jo--... .--
i-----'
-
- -.03
M=0.95
" ·~II till t I f II III fill f IIIWIII
"O~II ~jjJf IIIIII § II
.01
V
lL
o
V
v
-.01 V ./ -.02 V /
--
-.03 I Cy o M=I.03 I '-6 -4 -2 0 2 4 6 8 10 12 14 16 /8 20 2.2 Angle of attock,a,deg (b) M = 0.95 and 1.03.
Figure .19.- Continued.
,02 ,B,deg 0 0 0-5.1 .01 e------ ~
.,...---
..-[ C ~ u I -.0 I .0 I
/
/
D
l]/
V / -.01
/
C n
V
../ -.02
V
,.- V .--!
-,03 _I- -.04 .1 C y r:-.
~
o
M=I,18 4 6 8 10 12 14 16 18 20 22
-4 -2 o 2
Angle of ottock,a,deg (c) M = 1.18.
Figure 19.- Concluded.
~_] I tlJJUfH Rft III fH 111 j R II .
~ ..........
. 03 V
V
~ y-- ~ .02 b--
---
c n (3,deg 0 0 .0 I 0-5.1
o
v
Cy J I till e II UJ 111111 1 1114 II
-
,01 /' ./ .,/" C z .......... f-o .-/ o "\:J p- :--
--
f.-.--- :r--
---
-.01 V ......- .03
---
r-cl-'
f-- p- ---' I-- I-- .02 I--
---
en .01 o
-
:--0 y
C J I t III ell UJ II till j III~ I i
!...6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 ·22 Angle of attock ,a ,deg (a) M = 0.60 and 0.90.
Figure 20.- Lateral-directional characteristics of model without both vertical tails and with other surfaces undeflected. ~ = 0° and _5.1°.
·02 V l- h--
""
/ .01
l"'-c
""
1/
Cl
V
~
-
o ~ I---- 1----1-- I- -.01 f'- .04 V .03 1/ C .02 n V tJ- J-- tr-- /3,deg o 0 .01 D-5.1 o -0
. c, '~II ! III i I fH 1111111 t 1113 111111
CI_] IlUJIHH I11tll1111tlil
.04 //
yV
.03 /' V -I---" .02 I-- ~ C
-
n .01 o
C, _'~II till fffH 111.1111 till, II H II
:"'6 -4 -2 0 2 4 6 8 10 12 14 19 18 20 22 Angle of ollack,a,deg (b) M = 0.95 and 1.03.
Figure 20.- Continued.
,0 I ,....- )---
f.--1'
r-- tJ--
Cz
f--' b:-:::
"
-,01 ,05
L
V
L- ,04
V
V
./ .03
V
~V ~ j...--- C n ,02 1---' I-- I--
. -
,B,deg 0 0 .01 0-5.1 -.01 .1 C y 0 M=I.18 -4
-2 o 2 4 6 8 10 12 14 16 18 20 22
Angle of attock ,a ,deg (c) M = 1.18.
Figure 20.- Concluded.
C,O~II UtUOOfffi II [Jf[Q III~ II
....r
o K.
vV'
V --n .---c -.01 V / -.02 1/ C / n_.03 / !
-.04 / / -.05 {3,deg 0 0
/
-.06 o -5.1 -"-< J......
./ .2 I--i II- .1 C y o M=0.90 -.1
C"O~II tW mall I fHTIn~ I m II
o f'---..
L.--
-- z
-
V
-.01 1/ / -.02 / C "....
n_.03 / ,/' -.04 ,/ ,..- 't-- V -.05 V ./ -.06 .2 .1 C y o M=I.03 6 8 10 12 14 16 18 20 22 -2 o 2 4 Angle of allack,a,deg (a) M = 0.90 and 1.03.
Figure 21.- Lateral-directional characteristics of complete model with speed brakes open; other surfaces undeflected. ~_ = 0° and -5.1°.
-I: ,0 I r---
-
I----
p- it·
~ -fr-
o '-'
'-' I: -.0 I .01
o
~ l"- V
-
': -.01
L
L
-.02
s.V
L--
p--
V /
L
-.04
/
/
-.05
/
/
{3,deg -.06 h-
V
r-r- V
o -5.1
[v
-.07
.2
-c .
• 1
C
y
o
M=I.IS
-J. -4 -2
6 o 2 4 6 S 10 12 14 16 IS 20 22
Angle of ottock,a,deg (b) M = 1.18.
Figure 21.- Concluded.
o 1"-- t--- '" -.0 I /' 1/ -.02 V -.03 / V
v
-.05 V V h-- f3 ,deg -.06 !J- 0 o -5.1 -.07
~ '~I~ I jill ~ll t I t'~IIMU I-r------r------I till t~11 § II
c/o~11 un 1 11 bmM1Jf§ I ill=1
o f0 -.01 V / -,02 ) en / -.03 -.04 ......
V -.05 It-+- J- I-- h- -.06
~ _~I~ I f 111~f I t I i I~IIJJ I ~lnmn~I:111
'!6 - 4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of attock p. ,deg (a) M = 0.90 and 1.03.
Figure 22.- Lateral-directional characteristics of complete model with lower speed brakes open; other surfaces undeflected. ~ = 0° and -5.1°.
·01
r- ID S~ C f----"
-
r--
0 oJ
Q 'J
-.0 I
.01
r: h "" v
-.01
~
-.02
/
-
~'/
-.03 V /
//
rV"
V
/' -.05 L/ """";:D'"
V
-.06 El- ~
H r-
f-'""'" I----
...--
{3,deg -.07 Lit'"
a 0
o -5.1
-.08
.2
r 1-
-
ILl
.1
C
y r:-. r-.
o
~ . \: M=I.18
4 14
o 2 6 8 10 12 16 18 20 22
Angle of attack ,a,cJeg (b) M = 1.18.
Figure 22.- Concluded.
·04 ,03 --t.
-
Cz .02 .01 .03 -til::--
I- r-ct--
-
.02
r-
t-c b., C n t--t-- 1-6 .01
cJ I ~ III m It 111.1111 ~ 1111111~ II
. .
,04 r-.; -"l t-- ~ r--. F:: .03 ........,
f--' r----
Ir- r-
~ .........
C .02 z ---,a, .01 ..... ...-' lle,deg 8 ,deg Brakes .04 0 0 Closed --t--,b- o -10 20 Closed t-- N <> 0 20 Closed .03 r- 0 20 Open l- ""-!
t--. I--
- --
'"
-...., i ........
- .........
t>--
--
.02 --
."-., l- ...... , t---. ......
C n .........
"';..,.
"- .01 'tJ "- "-.,
"""
..........
:-...;
-
.....".
-.01
-
~ J I t III ~ I ~ I J IIIA.ill ~·III til ~ II
=-6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of attack,a,deg (a) M = 0.60 and 0.90.
Figure 23.- Lateral-directional characteristics of complete model with various Ba and Be, and with speed brakes open and closed. 13 = 0°; Bv = 0°, V r---..
.04
I"--
I?"-
=
>-- r--
.03 -
-
!'--- ...... r---, C .02 .01 .04 "- "- .03 'r-
--
.'-..
-...
.02 ......., r-......
C n ...... , ~ .01
""
I" C"':l
cyj lilll~lmU.lflllJlllfll HII
.04 r- j"--[
r--
.03
r--
r----
r--
p::
-- r--
I'-..!
C; .02 .01 8 deg 8a deg Brakes' e
0 6 6 Closed
.04 o -10 20 Closed I"-!
I'-- t-- <> 0 20 Closed l; 0 20 Open
J'I
.03 ,....
~ r-,.
I"-
-...
"- r- .02
--
"'-...
-
C ~
-
n
--
..........
~ :--.. ..", .01
--
-.1 0::::::::
--
~ ..........
-.01
Cy J IlllzlJI ~ I ~ UJ ~ III ~ III ~ III ~ II
~6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of ottock,a,deg (b) M = 0.95 and 1.03.
Figure 23.- Continued.
.04 <v .03 --< u :).........
[II-
r--
~
~
.02 C .01 \.:.
-.0 I .05 8 ,deg 8a ,deg Brakes e .J--.-.- 0 0 Closed ~ 1--- .04 0 -10 20 Closed
--
--C r--.
<> 0 20 Closed
...... 1'---- t:::.
0 20 Open I--..
.03 ,lr--......
>--- r----..
- "'-
i'--
-< (-...
.........
N
. 02 ........
~
I'----
--.
I'-" I'-- en ........
r-- ~ -- '-,
i'---
"'" I"- -......
~ .01 -...
r--: ~ ~
r. f.:- H
--,.
'-.,~
I'--
-.01 ........., ~ -.02
Cy ] I ~ III g III ~j.J I tlll~ IIIII
'~6 -4 -2 0 2 4 6 8 10 12 14 16 18 20 22 Angle of attock ,a,deg (c) M = 1.18.
Figure 23.- Concluded.
.04 ~ ~ .---t I---
f--< __ V
'------<
)-- r-:-c
r--
--< t---- ~n .03 V ~ ..-----l:
</,---- ----
r--<
.....[J------ t::::::-
-
,.--- -v
\----[
I.----- .02 tJ.------
r--
I--
r----
-( b---- I---r-- o r- ~
-
cb---- -.0 I .02
/
V
L .0 I
V
..d' ~
V
zV
o
,A: V ,V
/
V
V
V
V
-.01 V
n---
/---l
----
V
I-- ~V l.- V
V
l-- ./
V
V
/
-.03
V
8 ,deg 8a,deg e L 0 0
V
-10 20 ~ -.04 J--+- 0 0 20 f-- -.05 .2 ::y
"' 13'
M=0.60
-4 -2 o 2 4 6 8 10 12 14 16 18
20 22 Angle of attack ,a,deg (a) M = 0.60.
Figure 24.- Lateral-directional characteristics of complete mOdel with various 0a and Be; other surfaces undef1ected. ~ = -5.1°.
.05 .04 .'03 C .02 .0 I -- j}--- -.01 .0 I --0 I--- --r I-- ~p
V
-.0 I V /V l..---'
V
i,-"
,--- ---
1_ ~.
[./
I--c
I'-- I----
/
-.02
V
/
~ en
V
./ -.03
/"
V
/'
-.04
V
~e,deg /la,deg 0 '0 0 f/ -1'0 20 -.'05
P
V- 0 '0 20
-
-.06 .2 t-- ,.
--
,I C y M='O.90 18 20 22
-2 o 2 4 6 8 10 12 14 16
Angle of attack ,a ,deg (b) M = 0.90.
Figure 24.- Continued.
.06
v
~
----
/ .05
/
~ -< ~ ----~ f--" .
V b- I'--
. 04 i--' I-" ~ l.- 1"<: V-
v<
/' L:::---
v[
I- <V
..LV
.03
V
"~ l.----C C z I--- b----- .02 r-..
:-----
.-"J-/
,/
~ L
.01
r-----
-C V
r---
~ r-- ~ j..-C b---"" Ir- ~ f-- f-- -.01 .01
L
v
-.01 -.02
vI-" V
C n -.03
v
v
-.04
/v Se,deg 8a,deg __
~ 0 0 0 f--+--+---+--+-----If---+---I--+--+--i-+----t---+--+-=+-""""'-I---+---+---+--+--I--f---/ 0 - 10 20 -.05
.-cr- 0 0 20
--
-.06 .2 t:::-
-
C y -u M=0.95 -4 o 2 4 6 8 10 12 14 18 -2 16 20 22 Angle of attack ,a,deg (c) M = 0.95.
Figure 24.- Continued.
.05 t:::" .04
-- v
V r---..
1>-- ---
N
.- ---- r---. t--..
-I---<
1--1- ~ ----0 b-- I--
<I>-- J--I
~ .03 I-"
--
I-- I-- It-- X>
'"
C .02
z
.01 -C l---- I----.
~ F:::::
1-----1 t-o
o
.\-- I--<
-
-.01 .01
/
o
/
VI7
-r -.0 I ,
//
-.02
.f/
( -<..
'--- ~
N ./ V
:..::::::<: r--<>-.
-
V
/V
-.04
/ 8 ,deg 8 ,deg
e a .v 0 0
..... V
-10 20 -.05 0 20
<>
---
-.06 .2 t4il Cy .1 ~ M=I.03
-2 o 2 4 6 8 10 12 14 16 18 20 22
-4 Angle of attack ,a,deg (d) M = 1.03.
Figure 24.- Continued.
.04 --'"
. r-----
v- t-----.
.03 ~ I---f I---
1'0
1--- .02
Cz
.01 I"'.
;-- -l---
a
-.01 .01 ..
.fl
a
V
V
---r- r-
-
I-- J.r--- -.01 I--- J.----
.-
to
-.02
V
v
V
/
L C -.03 n
V
V~
v
---.:- p-
r--
N- j,--
r-
t--<- ~
--"
-.04
-
..(V
v
V
-.05 V
V 8 ,deg 8 ,deg
e a
p
a a
I-- --<b------ -10 20 -.06
<> a 20
-.07 .2 A pvo v C y .1 M=I.18
-4 -2 a 2 4 6 8 10 12 14 16
18 20 22 Angle of attack ,a,deg (e) M = 1.18.
Figure 24.- Concluded.
.09
--
--
Lo t::::::::,
.08
----
/
£:i ~ I'"
V
~ t::::-----.. ~
.07
""'-..
--
t'-_
-
r--
(p I
.06
I
)
t--
-
.05
a=IO°
.04
Complete model
- - - Horizontal tail off
o Complete model,brakes open
.08
~f-""
-
r--
./ ~ ~
.07
-.....
V 0
1'--,
~ V
~ L j....---"' ...........
(
~ V
/'" ~ I'"
--
~
V-
I---
-
.05
a =0°
.7 .8 .9 1.0 1.1 1.2
Mach number,M
Figure 25.- Variation with Mach number of iift-~Urve slopes. Surfaces undeflected unless otherwise noted. ~ = 0°.
.2
Complete model
--
----
Horizontal tai I off
Complete model, brakes open
o
-
r-----
r-....
--------
1--- '-..
-
r---
-
--
.. - ,-..
-4
....- •
V
-........
~
"t:
V
C =0.8
L
'"
-.6
.8 .9 1.0 I .1 1.2
.6 .7
Mach number 1 M
.2
- -
r--...
.....
o
...........
(~
- -
- --
r--
-----
~
--
i'...
-.2
'U
C = 0
L
.7 .8 .9 1.0
1.1 1.2
Mach number 1M
Figure 26.- Variation with Mach number of static longitudinal stability parameter. Surfaces undeflected unless otherwise noted. ~ = 0°.
-.2
-.1
-
-
1 .1
.7 .8 .9 1.0 1.2
Mach number, M
-.04
f- C = 0
L
r
-.03
I--
l----
~
---
~
~
..........- I--
-....:.:.
~ .............
r--
1'--...
/ i--
-I--
V'
J
C =0.8
L
-.0 I
o
.8 1.1
.6 .7 .9 1 .. 0 1.2
Mach number,M
Figure 27.- Variation with Mach number of longitudinal control parameters for complete model at ~ = 0°.
Surfaces other than horizontal tail undeflected.
u
o
Brakes closed
o Brakes open
.........
(L/D)mox
""
o
.24
.20
()
.16
Co,o
.12
/'
.08
/
---
.04
.8 .9 1.0
.7 1.1 1.2
Mach number, M
Figure 28.- Variation with Mach number of drag and maximum lift-drag-ratio parameters for complete model at ~ = 0°. Surfaces undeflected unless otherwise noted.
Complete model
Both vertical tails off
Lower vertical ta i I off
o Complete model, brakes open
·0 I
a= 16
-
~
u
--
-
-
-
---- -
,- 1--.
~
,,7
.8 .9 1.0 1.1 1.2
Mach number, M
.02
D
£ D--
.0 I
u
C
f-- -
-- -
-
nf3 -
-
-
o
- r--
a=O
-01
· 6
.7 .8 .9 1.0
1.1 1 .. 2
•
Mach number,M
Figure 29.- Variation with Mach number of static directional stability parameter. Surfaces undeflected unless otherwise noted.
Complete model
- -- Both vertical tails off
Lower vertical ta iI off
o Complete model, brakes open
.. 002
r-....
o
-.....::::::
l"-
~
LlS""
Cl(3
--
v....."
~ ~ ~r--..
I'-- -...
.........
,...
....... K / L~ r.
........
-.002 D __ - ---..::::-'
'/
~ V
~(
~ -
V
---....... )
[\
r-
--
VI
a = 16
V
~
-.004
,,7
.8 ,9 1.0 1.1 1.2
.6
Mach number, M
.002
fo-
--
-
a= 0°
-.002
.7 .8 .9 1.0 1.1 1.2
.6
Mach number, M
Figure 30.- Variation with Mach number of effective dihedral parameter. Surfaces undeflected unless otherwise noted.
a,deg
o
.002
.001
~ ...........
""
r---
o
--=
.-
r---
-001
, .6
.7 .8 .. 9 1.0
1.1 1.2
Mach number, M
.003
-
-
~
t---
-
--
.001
o
1.0
.6 .7 .8 .9 1.1 1.2
Mach number,M
F.igure 31.- Variation with Mach number of lateral control parameters for complete model at ~ = 0 • Surfaces undeflected except for horizontal tail as a roll control.
Brakes closed
o Brakes open
o
-.004
..0.
CD -
~
en
Bv
-.008
a= 16
.7 .8 .9 1.0
1.1 1.2
Mach number, M
o
-.004
-
--0
-.008
a=O°
- 012
· .6
.7 .8 .9 1.0
1.1 1.2
Mach number,M
Figure 32.- Variation with Mach number of yawing 'moment due to vertical-tail deflection for complete model at ~ = 0°. Horizontal surfaces undeflected.
Brakes closed
o Brakes open
.001
,D
V-
r---
u
---
---
a= 16
-001
.7 .8 .9 1.0 I. I
· .6 1.2
Mach number ,M
.001
"'\
a=O
-.001
1.1 1.2
.7 .8 .9 1.0
.6
Mach number,M
Figure 33.- Variation with Mach number of rolling moment due to vertical-tail deflection for complete model at ~ coo. Horizontal surfaces undeflected.