Effects of Wall to Stagnation Temperature Ratio on Hypersonic Corner Flows

Abstract

Numerical solutions of laminar, hypersonic, viscous, high temperature, perfect gas flows over compression corners are obtained. The effects of corner angle (θw) and wall to stagnation temperature ratio (Tw/T0) on flow variables, especially on surface pressure distributions and surface heat transfer rates are investigated. A three dimensional, compressible, Reynolds averaged thin layer Navier-Stokes code is used. The numerical method is a stream-wise upwind finite difference method with Lower Upper-Alternating Direction Implicit (LU-ADI) decomposition. Eight different free-stream and wall conditions and seven different corner angles ranging from θw=5o to 24o are considered. The results are presented in terms of boundary layer properties, surface pressure distribution, heat transfer rates and compared with the available experimental results and theory.