SHOCK-WAVE BOUNDARY LAYER INTERACTIONS AT HYPERSONIC SPEED BY AN IMPLICIT NAVIER-STOKES SOLVER/

An implicit Navier-Stokes solver has been used to calculate steady-sta te solutions for several typical hypersonic geometries. Particular att ention was paid to the resulting complex interactions between the shoc k waves and the boundary layers. The numerical method was based on eit her an upwind Galerkin finite-volume approach or a symmetric TVD exten sion for the convective fluxes, with a centred Galerkin finite-element solution of the viscous fluxes. The computational grid consisted of s tructured finite elements within the boundary layer region and unstruc tured triangular elements elsewhere. Results are presented for the cas e of a compression ramp in two different flow situations. The first co ncerns a high Reynolds number flow while the second is at a higher Mac h number but a lower Reynolds number. Comparisons with experimental da ta are given. Subsequently computed results for two generic canopy flo ws over a double ellipse are also presented. These have been calculate d for wind tunnel conditions at zero angle of attack. Comparisons show that the skin heat transfer and the pressure coefficients are in agre ement with the shape of those found in the experiments. The importance of calculating equilibrium conditions in order to establish maximal m argins is clearly indicated.