HYPERSONIC NONEQUILIBRIUM NAVIER-STOKES SOLUTIONS OVER AN ABLATING GRAPHITE NOSETIP

The general boundary conditions, including mass and energy balances, o f chemically equilibrated or nonequilibrated gas adjacent to ablating surfaces have been derived. A computer procedure based on these condit ions 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 condit ions was developed. The solutions of the GASP code with various surfac e boundary conditions were obtained and compared with those of the ASC C (ABRES Shape Change) code, and the effect of nonequilibrium gas as w ell as surface chemistry on surface heating and ablation rate were exa mined.