Hypersonic viscous shock-layer flows including leeside separation

Abstract

The three-dimensional, laminar, viscous hypersonic flowfield over blunted cones at large angles of attack, including crossflow separation, has been solved using both viscous shock-layer and parabolized Navier-Stokes equations. A computer code has been developed using this technique, and calculations were made for two test cases, which typically encompass laminar re-entry flow conditions. Case 1 considered low Mach number (10) and high Reynolds number (2x 10/ft) at moderate angle of attack (10 deg). Case 2 considered high Mach number (25) and low Reynolds number (7256/ft) at large angle of attack (35 deg). The results have been compared with a complete parabolized Navier-Stokes solution, and for case 1, the aerodynamic coefficients have been compared with available experimental data. The comparisons indicate good agreement for wall pressure, both longitudinal and crossflow skin-friction coefficients and aerodynamic coefficients. A fast implicit iterative technique known as the Pseudo Elimination Method has been used to solve the parabolized Navier-Stokes equations, and the computing time has been reduced by 35%. The computing times required indicate that the present code obtains complete flowfield solutions in the shortest possible time, thus making it an ideal tool for design analysis of lifting re-entry vehicles.