Shuttle Orbiter Re-Entry Flowfields at High Angle of Attack

An analysis of the continuum inviscid and boundary-layer flowfields around various configurations representative of an early version of a space shuttle orbiter re-entering the atmosphere at 40° and 60° angle of attack is presented. The inviscid flow fields were predicted by 2-D time-dependent and 3-D steady finite difference/artificial viscosity techniques, together with a 2-D shock layer analysis method. Boundary-layer flow and heating rates were computed with an integral matrix technique. Configurations which were considered in the analysis included: 1) 2-D flat plate representations of the flat underside of the orbiter fuselage, 2) 2-D orbiter fuselage cross sections, 3) 2-D orbiter wing airfoils, and 4) a 3-D straight-wing orbiter configuration. Theoretical results correlated satisfactorily with pressure and heat transfer data on flat plates and wings (including shock intersection regions).