Computation of nonequilibrium flows using PNS equations 13; 13;

The laminar, hypersonic flow of five-species (N2, O2, NO, N, O) nonequilibrium air over a 10 degree axisymmetric cone is computed using a non-iterative, implicit finite-difference scheme. The numerical algorithm is based on central differencing of the inviscid and viscous fluxes. Two gas models are considered in this study - one in which the constituent species are both calorically and thermally perfect and the other in which the constituent species are only thermally perfect. The effects of the two gas models and the types of wall boundary conditions on the computed solution are studied and discussed