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Aerodynamic heating on AFE due to nonequilibrium flow with variable entropy at boundary layer edgeA method of predicting the aerobrake aerothermodynamic environment on the NASA Aeroassist Flight Experiment (AFE) vehicle is described. Results of a three dimensional inviscid nonequilibrium solution are used as input to an axisymmetric nonequilibrium boundary layer program to predict AFE convective heating rates. Inviscid flow field properties are obtained from the Euler option of the Viscous Reacting Flow (VRFLO) code at the boundary layer edge. Heating rates on the AFE surface are generated with the Boundary Layer Integral Matrix Procedure (BLIMP) code for a partially catalytic surface composed of Reusable Surface Insulation (RSI) times. The 1864 kg AFE will fly an aerobraking trajectory, simulating return from geosynchronous Earth orbit, with a 75 km perigee and a 10 km/sec entry velocity. Results of this analysis will provide principal investigators and thermal analysts with aeroheating environments to perform experiment and thermal protection system design.
Document ID
19920005802
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ting, P. C.
(Lockheed Engineering and Sciences Co. Houston, TX., United States)
Rochelle, W. C.
(Lockheed Engineering and Sciences Co. Houston, TX., United States)
Bouslog, S. A.
(Lockheed Engineering and Sciences Co. Houston, TX., United States)
Tam, L. T.
(Lockheed Engineering and Sciences Co. Houston, TX., United States)
Scott, C. D.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Curry, D. M.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1991
Publication Information
Publication: ESA, Aerothermodynamics for Space Vehicles
Subject Category
Aerodynamics
Accession Number
92N15020
Distribution Limits
Public
Copyright
Other
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