Book Description

Measurements are presented for boundary-layer-induced pressure gradients on a flat plate in air at a Mach number of 9.6 and for the drag of thin wings at a Mach number of 6.8 and zero angle of attack. The investigation was conducted in the Langley 11-inch hypersonic tunnel, and the pressure measurements at a Mach number of 9.6 were made in the presence of substantial heat transfer from the boundary layer to the wall.