Solution strategies and heat transfer calculations for three-dimensional configurations at hypersonic speedsA procedure which reduces the memory requirements for computing the viscous flow over a modified Orbiter geometry at a hypersonic flight condition is presented. The Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) code which incorporates a thermochemical nonequilibrium chemistry model, a finite rate catalytic wall boundary condition and wall temperature distribution based on radiation equilibrium is used in this study. In addition, the effect of choice of 'min mod' function, eigenvalue limiter and grid density on surface heating is investigated. The surface heating from a flowfield calculation at Mach number 22, altitude of 230,000 ft and 40 deg angle of attack is compared with flight data from three Orbiter flights.
Document ID
19920065269
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Weilmuenster, K. J. (NASA Langley Research Center Hampton, VA, United States)
Gnoffo, Peter A. (NASA Langley Research Center Hampton, VA, United States)