Computation of Görtler Vortices in Separated Hypersonic Flows

In concave boundary layers as well as in separated flows counter-rotating streamwise vortices appear if certain flow conditions are satisfied. These socalled Görtler vortices lead to significant transversal heat flux fluctuations in hypersonic flows. Until now numerical simulations of such instabilities have been carried out only for simplified geometries. Nevertheless, fully three-dimensional computations are of special interest for hypersonic re-entry vehicles especially on deflected control surfaces (flaps). For the present investigation a lifting body vehicle is chosen to show the capability of Navier-Stokes codes to simulate the influences of Görtler vortices at Mach 6 and Re=3.1x10*. Resolution of laminar vortices is possible by generation of local grids in the flap region with extensive spanwise grid refinement