Computation of wall heat fluxes in hypersonic inlet flows

Abstract

Within the frame of the German Collaborative Research Center SFB 253 “Fundamentals of Design of Aerospace Planes”, generic supersonic and hypersonic engine inlet configurations are investigated both numerically and experimentally. This paper presents an overview of the ongoing work on the numerical simulation of high-speed inlet flows solving the complete Reynolds averaged Navier-Stokes equation with a block-structured, cell-centered finite-volume method. The turbulence model is Wilcox’s low Reynolds number k − ω model with some extensions for modeling high-speed wall-bounded flows and separation regions. The first configuration involves a supersonic inlet with interior compression and the development of a subsequent shock train. This test case is mainly used to demonstrate the present state of a newly implemented advanced multigrid method for supersonic turbulent flows. Of recent interest is the accurate prediction of wall heat transfer rates in the second test configuration. This configuration is a heated compression ramp model which is presently investigated experimentally in a shock tube to assess the influence of the wall temperature on boundary layer separation behavior.