EAS 4710 Aerospace Design 2

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EAS 4710 Aerospace Design 2
5. Hypersonic Aerodynamics
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General Mission Types
M
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Development of manned spacecraft
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Gemini capsule in a ballistic range
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Mars lander in a ballistic range
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Apollo Command Module
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Genesis Mission Reentry
Send a spacecraft to collect pristine material
from the solar wind and then return the samples
to Earth for analysis
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Genesis sample return capsule
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Genesis capsule entry conditions
Reentry conditions on September 8, 2004 Mass
225 kg Diameter 1.52 meter Speed 11.0 km/s
Entry angle 8.0 degrees Heat-shield
Carbon-Carbon Spin rate 15/s Peak heating 750
W/cm2 BW/CDA1.2kPa
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Genesis capsule on the ground
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Stardust sample return capsule
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Stardust capsule reentry
Reentry conditions Date January 15, 2006
(night time) Mass 45.8 kg Diameter 0.811
meter Speed 12.8 km/s (at 135 km) Entry angle
8 degrees Heat-shield material Phenol
impregnated Carbon Sample return comet P/Wild 2
dust
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Shock aerodynamics
Shock wave
V2
d
V1
q
V1
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The hypersonic approximation
The shock Hugoniot relation is

e1/6 g2 1.4 e1/9 g2 1.25 e1/21 g2 1.1
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Aerodynamics in the Newtonian approximation
N
P (lower surface)
friction
M


A
a
P (upper surface)
base drag
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Lift to drag ratio
Volume parameter tu2/3 /S
0 .2 .4 .6 .8
1
8 6 4 2 0
L/D
slender body, CF0.001
X-15
bluff body, CF0.1
Space shuttle
NASA experiments
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Aerodynamics, L/Dka(M3)/M
15 L/D 10 5 0
CV-880
ka4
B-58
F-16E
ka3
XB-70
SR-71
space shuttle
X-15
0 1 5
10 M
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Panel method using Newtonian Flow
V (free stream velocity)
n (unit normal vector)
Elemental body panel
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Application of the Newtonian method
Modified-Newtonian correction term
cp 0
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Skin friction on a space plane vehicle
Stagnation point location
V
ns
s
Panel i
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The X-24C under test at AEDC
Calculations of drag polar and pitching moment
compared well to test and Navier-Stokes CFD
calculations with several million points
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X-24C panel model
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X-24C L/D vs angle of attack
L/D
Angle of attack (deg.)
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X-24C lift and drag coefficients
CL and CD
Angle of attack (deg.)
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X-24C pitching moment coefficient
Trim point
Cm
Angle of attack (deg.)
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NASA X-43A Scramjet Vehicle
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Soviet space plane
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Australian Navy recovers space plane
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Structures and heating
0 400 800 1600
3200 T (F) 0 2 3 4 5
6 7 M
1000
50ksi ACC
UTS/r (in x 10-3)
Superalloys
X-15 (Inconel)
Concorde (Al)
XB-70 (SS)
RCC (Space Shuttle)
SR-71 (Ti)
ceramics, carbides, and oxides
0
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Flight corridor
Z (kft) 300 200 100 0
Space shuttle
X-15
q30 psf q100 psf q1000 psf
SR-71
XB-70
HCV
Concorde
0 10 20 M 30
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Cruise altitude
150 Z (kft) 100
50 0
(W/S)/CL
300 psf
500 psf 1000 psf 1500 psf
SR-71
HCV
X-15
XB-70
Concorde
0 2 4 6 8
10 M
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Paneling a reentry craft
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The generic surface panel
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Blunt reentry bodies
Afterbody cone angle, f1
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CD,0 of reentry capsule shapes
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Blunt reentry bodies
Angle of attack limitations when using analytic
Newtonian solution for axisymmetric bodies
Manned capsule f130o
Unmanned planetary lander f160o
amax
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Lift and drag definitions
Max a to keep only the heat shield to windward
A
N
D
L
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Lift and drag of reentry capsules
Angle of attack limitation
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Lift to drag ratio of reentry capsules
Angle of attack limitation
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Capsule forces along trajectory
R
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Blunted cone reentry vehicles
Nose bluntness mitigates reentry heating effects.
Charred ablative heat shield from the first KH-4
CORONA mission. This heat shield was supposed to
fall off after parachute deployment.
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Bluntness effects on drag coefficient
Small drag penalty for reducing nose heating