Hypersonic nonequilibrium Navier-Stokes solutions over an ablating graphite nosetip

The general boundary conditions, including mass and energy balances, of chemically equilibrated or nonequilibrated gas adjacent to ablating surfaces have been derived. A computer procedure based on these conditions was developed and interfaced with the Navier-Stokes solver GASP (General Aerodynamics Simulation Program). A test case with a proposed hypersonic test-vehicle configuration and associated freestream conditions was developed. The solutions of the GASP code with various surface boundary conditions were obtained and compared with those of the ASCC (ABRES Shape Change) code, and the effect of nonequilibrium gas as well as surface chemistry on surface heating and ablation rate were examined. Nomenclature A = area, m2 B' = quantity defined in Eq. (7) CH = #-type heat-transfer coefficient, kg/m2 • s CM = mass-transfer coefficient

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