Thermochemical nonequilibrium issues for earth reentry of Mars mission vehiclesThe thermochemical environment about an axisymmetric 60-deg sphere-cone with a circular aft skirt is computed using the Langley Aerothermodynamic Upwind Relaxation Algorithm. Earth entry at 12 km/sec is examined at 70-km and 80-km altitude for two vehicle base radii of 2 m and 6 m. These four test cases bracket some proposed scenarios for earth reentry of a manned Mars mission aerobrake at this velocity. Thermochemical nonequilibrium results are examined for each case and compared with thermal equilibrium results produced by artificially accelerating vibrational relaxation rates and with equilibrium results produced by a viscous shock layer method.
Document ID
19900051346
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mitcheltree, R. A. (NASA Langley Research Center Hampton, VA, United States)
Gnoffo, P. A. (NASA Langley Research Center Hampton, VA, United States)