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.