Viscous Shock Layer Analysis of Hypersonic Flows Over Long Slender Vehicles

A method for solving the viscous shock-layer equations for hypersonic flows over long slender bodies is presented. The governing equations are solved by employing a spatial-marching implicit finite-difference technique. The two first-order equations, continuity and normal momentum, are solved simultaneously as a coupled set. This method yields a simple and computationally efficient technique. Flows past hyperboloids and sphere cones with body half angles of five to 35 degrees are considered. The flow conditions included are from high Reynolds numbers at low altitudes to low Reynolds numbers at high altitudes. Detailed comparisons have been made with other predictions and experimental data for slender body flows. The results show that the coupling between the continuity and normal momentum equations is essential and adequate to obtain stable and accurate solutions past long slender bodies. Both the Cebeci-Smith and Baldwin-Lomax turbulence models are found to be adequate for application to long slender bodies. Using the corrected slip models, the viscous shock-layer predictions compare quite favorably with experimental data. Under chemical nonequilibrium conditions, the surface catalytic effects can significantly influence the surface heat transfer