Heat Transfer Due to Shock Wave Turbulent Boundary Layer Interactions on High Speed Weapon Systems

摘要: Abstract : Three-dimensional shock wave turbulent boundary layer interactions caused by a fin-plate configuration were investigated experimentally and analytically. Wind tunnel tests conducted at Mach number of 3.71 the studied near full scale conditions mounting one several fins normal to sidewall in naturally turbulent, 6 inches thick layer. Tests primarily with sharp leading edge planar fin, although blunt swept also used. The experimental data used develop new analytical correlation procedures.