Direct Simulation of Hypersonic Crossflow Instability on an Elliptic Cone

Abstract

Direct numerical simulation is performed on a 38.1% scale Hypersonic International Flight Research Experimentation Program Flight 5 forebody to study stationary crossflow instability. Computations use the US3D Navier–Stokes solver to simulate Mach 6 flow at Reynolds numbers of and , which are conditions used by quiet-tunnel experiments at Purdue University. Distributed roughness with point-to-point height variation on the computational grid and maximum heights of is used with the intent to emulate smooth-body transition and excite the naturally occurring most unstable disturbance wavenumber. Cases at the low-Reynolds number condition use three grid sizes, and hence three different roughness patterns, and demonstrate that the exact flow solution is dependent on the particular roughness pattern. The same roughness pattern is interpolated onto each grid, which yields similar solutions, indicating grid convergence. A steady physical mechanism is introduced for the sharp increase in wall heat flux seen in both computations and experiment at the high-Reynolds number condition. Evolution of disturbance spanwise wavelength is computed, and is found to be more sensitive to Reynolds number than roughness, indicating that the disturbance wavelength is primarily the naturally occurring, flow-selected wavelength for these cases.