Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds

摘要

Pitot-pressure profiles and surface pressure measurements have been obtained at four axial stations along the center lines of space shuttle straight-wing and delta-wing orbiters at angles of attack from 20 deg to approximately 60 deg and Mach numbers of 20.3 (helium) and 6.8 (air). The results show that the Mach number at the edge of the boundary layer is best predicted by tangent-cone theory up to shock detachment.