A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack

Relationship of shock standoff distance, at sonic and stagnation points, to body geometry of blunt bodies at zero angle of attac

Estimation of shock layer thickness and pressure distribution on a delta wing-body space shuttle orbiter

Calculation of shock inclination angle and surface pressure coefficient in vertical plane of symmetry of bodies at angle of attack related to delta wing-body space shuttle orbite

Effects of mass addition on blunt-body boundary-layer transition and heat transfer

The model bodies tested at Mach number 7.32 were hemispheres, blunt cones, and spherical segments. The mass addition consisted of air ejected through porous forward surfaces of the models. The experimental data consisted of heat transfer measurements from which boundary layer transitions were deduced. The data verified various applicable boundary layer codes in the laminar and transitional flow regimes. Empirical heating rate data correlations were developed for the laminar and turbulent flow regimes