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SPACE LAUNCH SYSTEM
National Aeronautics and Space Administration
www.nasa.gov/sls
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Base Heating Test: Experimental Operations and Results
Aaron Dufrene, Matthew MacLean and Michael Holden CUBRC Inc. Aerosciences
Manish Mehta and Mark Seaford
NASA Marshall Space Flight Center Aerosciences Branch
Date: 1/5/2016
https://ntrs.nasa.gov/search.jsp?R=20160001817 2018-09-12T09:31:59+00:00Z
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2% SLS Base Heating Model
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SLS Vehicle
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ATA-002 SLS Model Propulsion Performance
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ATA-002 Similarity Parameter: Plip/Pinf
0
1
10
100
1,000
10,000
100,000
0 50 100 150 200 250
RS-‐25 Plip/Pinf
Altitude, kft
FlightATA-‐002 Integrated StackATA-‐002 Core Only
Core engine Plip/Pinf vs. altitude
0.1
1
10
100
1000
0 50 100 150 200SR
B Plip/Pinf
Altitude, kft
FlightATA-‐002 Integrated Stack
Solid rocket motor Plip/Pinf vs. altitude
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ATA-002 Similarity Parameter: O/F Ratio
0.0
1.0
2.0
3.0
4.0
5.0
6.0
7.0
1 10 100 1,000 10,000
O/F Ratio
RS-‐25 Plip/Pinf
ATA-‐002 Integrated StackATA-‐002 Core Only
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SLS Base Heating Model Instrumentation Layout
Heat Transfer (185)
Pressure (47)Radiometers (7)
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LENS Velocity/Altitude Capabilities
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ATA-002 Test to Flight Condition Comparisons
0.0
0.6
1.2
1.8
2.4
3.0
3.6
4.2
4.8
5.4
6.0
0 50 100 150 200 250
Mach Num
ber
Altitude, kft
FlightATA-‐002 Integrated StackATA-‐002 Core Only
0
200
400
600
800
1,000
1,200
0.0 1.0 2.0 3.0 4.0 5.0 6.0
Dyn
amic
Pre
ssur
e
Mach Number
FlightATA-‐002 Integrated StackATA-‐002 Core Only
0
500
1,000
1,500
2,000
2,500
3,000
3,500
0 50 100 150 200 250
Freestream
Total Tem
perature
Altitude, kft
FlightATA-‐002 Integrated StackATA-‐002 Core Only
0
200
400
600
800
1,000
1,200
0 50 100 150 200 250
Dyna
mic Pressure
Altitude, kft
FlightATA-‐002 Integrated StackATA-‐002 Core Only
Mach number vs. altitude
Total temperature vs. altitude Dynamic pressure vs. altitude
Dynamic pressure vs. Mach number
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Aft-Body Heat Transfer vs. Freestream Pressure Data
0.0010.010.11
Aft-‐Bo
dy Heat Transfer
Freestream Pressure (psi)
19 2021 2324 2526 2728 2930 3233 3435 3637 3839 4041 4243 4445 4647 4849 5052 5354 5556 5758 5960 6162 6364 6566 6768 7172 7374 7576
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Surface Aerothermal Predictions & Data for 70kft Condition
-‐5.000
0.000
5.000
10.000
15.000
20.000
25.000
-‐1
0
1
2
3
4
5
6
7
0 10 20 30 40 50 60 70
Heat T
ransfer & Pressure
Distance
PressureLaminar Heat TransferTurbulent Heat TransferRun 15 HTRun 15 PressureSLS OML
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CFD Calculation of Core-Only Configuration
150 kft conditions (Run 26)
Heat Flux Contours Line cuts across symmetry plane Heat Flux Contours
Line cuts across symmetry plane
100 kft conditions (Run 32)
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Core-only Aerothermal Test Data for 150kft and 100kft
0
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
0.18
0.2
-‐3 -‐2 -‐1 0 1 2 3
Pressure (p
si)
Position (in.)
Run 26
Run 32
0
2
4
6
8
10
12
14
16
-‐3 -‐2 -‐1 0 1 2 3
Heat Transfer (BT
U/ft2 ·∙s)
Position (in.)
Run 26
Run 32
Pressure vs. Radial Distance Heat Transfer vs. Radial Distance
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Region Specific Heat Transfer Measurments
0.0010.010.11
Base Cen
ter H
eat Transfer
Freestream Pressure (psi)
19 2021 2324 2526 2728 2930 3233 3435 3637 3839 4041 4243 4445 4647 4849 5052 5354 5556 5758 5960 6162 6364 6566 6768 7172 7374 7576
0.0010.010.11
EMHS
Heat Transfer
Freestream Pressure (psi)
19 2021 2324 2526 2728 2930 3233 3435 3637 3839 4041 4243 4445 4647 4849 5052 5354 5556 5758 5960 6162 6364 6566 6768 7172 7374 7576
Base center heat flux EMHS heat flux
0.0010.010.11
SRB Ba
se Heat Transfer
Freestream Pressure (psi)
19 2021 2324 2526 2728 2930 3233 3435 3637 3839 4041 4243 4445 4647 4849 5052 5354 5556 5758 5960 6162 6364 6566 6768 7172 7374 7576
SRM base heat flux
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Nominal BHS Heating Spatial Distribution from 50 kft-210 kft
0 0.5 1 1.5 2 2.5
CS Base He
at Tran
sfer
Position from Center (in.)
50 60
70 80
90 100
110 120
130 130
140 160
150 170
170 190
190 210
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Freestream Flow Effects on BHS Heating Spatial Distribution
0
2
4
6
8
10
12
14
0 0.5 1 1.5 2 2.5
CS Base He
at Transfer
Position from Center (in.)
Mach 5.1, 150kft, To=1610°RMach 5.1, 160kft, To=1650°RMach 5.1, 170kft, To=560°RNo Flow, 150 kftNo Flow, 170 kft
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Chamber Pressure Effects on BHS Heating Spatial Distribution
0
1
2
3
4
5
6
7
8
9
10
0 0.5 1 1.5 2 2.5
Core Only Ba
se Heat Transfer
Position from Center (in.)
80% Pc
60% Pc
40% Pc
20% Pc
Core only heating distribution
0
2
4
6
8
10
12
14
16
18
20
0 0.5 1 1.5 2 2.5
CS Base Heat Transfer
Position from Center (in.)
90% Pc
60% Pc
50% Pc
30% Pc
Full-Stack heating distribution
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Base Heat Flux Data Interpolation at 120 kft
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Base Heat Flux Contour Plots
120 kft Condition with 2-deg Gimballed Nozzles
(Run 71)
120 kft Condition at 4 deg AoA (Run
62)
120 kft Nominal Condition (Run
64)
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Unsteady Base Heat Transfer Measurements
0
5
10
15
20
25
20 40 60 80 100
Heat T
ransfer
Time (ms)
Full Stack, M4.2CS, M5.1CS, no flow
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Base Pressure Measurements
0
0.2
0.4
0.6
0.8
1
1.2
1.4
40 90 140 190
Pressure
Altitude (kft)
Mid Base Vert.Base CenterMid Base Hor.Base PeripherySRB1 InboardSRB2 Inboard
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
40 90 140
Pressure (p
si)
Altitude (kft)
Mid Base Vert.Base CenterMid Base Hor.Base PeripherySRB1 InboardSRB2 Inboard
Base Pressure Normalized base pressure by dynamic
pressure
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IR Radiometer Measurements
0.001 0.01 0.1
Irradian
ce
Freestream Pressure
CS Only CS OnlyCS Only CS, 1/2 PcCS, 3/4 Pc CS, 1/4 PcCS, Mach 5 CS OnlyCS, cold Mach 5 CS, Mach 5FS, Mach 4 FS, Mach 4
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Imaging of 2%-scale SLS hot-fire test at various conditions with full-stack configurations and core-only configuration
Visible camera, top view, 70kft, full-stack
Schlieren side view, 100 kft, full-stack
Long-wave IR, Top view, 170 kft, Core
only
Imaging
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Conclusions
u ATA-002 test operations, instrumentation layout and test matrix and conditions were described.
u Nominal and off-nominal test results are described.
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