Turbulent boundary layer flow over re-entry bodies including roughness effects

Hypersonic turbulent boundary layer flow over a spherically blunted cone has been computed using both integral and finite difference methods. The roughness effects are computed by appropriate correlations in the integral method and by modifying the wall boundary condition in the finite difference method. The methods are evaluated by comparing the predictions with experimental data obtained in wind tunnels at free stream Mach number of 5 and unit Reynolds numbers of 10 and 20 million per foot with surface roughness heights of 0.3 and 10 mil. Results for the heat transfer are presented. The comparisons indicate that the integral method can be used with confidence in the aerodynamic analysis of re-entry bodies.