Development and Validation of an Axisymmetric Navier-Stokes Solver for Hypersonic Flows

This note describes the development of an axisymmetric Navier-Stokes solver suitable for the computation of hypersonic flows. The governing equations in axisymmetric form are integrated by means of a time marching Finite Volume shock capturing method for structured multiblock grids whit cell centered locations of the unknowns. Different inviscid flux function formulations. in the context of high resolution upwind TVD schemes, have been implemented, and their respective performances assessed for the computation of laminar viscous flows in hypersonic regime. Numerical solutions of the axisymmetric Naier-Stokes equations are presented for hypersonic bodies in reentry configurations. A study of grid convergence, reliability and accuracy has been carried out, for two Hyperboloid Flare configurations, and for several Cone Flare configuration, at different Reynolds number, for which experimental data obtained at VKI exist. Grid convergence was achieved for most cases, although further refining in the separation zone is desirable.