Numerical Simulation of Steady Supersonic and Hypersonic Flows over Simple Bodies of Revolution. Aero Report 9902

This paper reports on numerical results for supersonic and hypersonic steady flows over axisymmetric blunt bodies. Two-dimensional compressible Navier- Stokes equations are solved using a high- resolution upwind Roe’s scheme. A modification to the boundary conditions and the implementation of Harten’s entropy fix is proposed to improve the robustness of the code, which is then tested on an axisymmetric spike, cone and cylinder at freestream Mach numbers of 2.21, 6.00 and 30.00