Heat Transfer Due to Shock Wave Turbulent Boundary Layer Interactions on High Speed Weapon Systems
Final rept. Jan 1973-Apr 1974
MCDONNELL AIRCRAFT CO ST LOUIS MO
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Three-dimensional shock wave turbulent boundary layer interactions caused by a fin-plate configuration were investigated experimentally and analytically. Wind tunnel tests were conducted at a Mach number of 3.71 and the interactions were studied at near full scale conditions by mounting one of several fins normal to the tunnel sidewall in the naturally turbulent, 6 inches thick sidewall boundary layer. Tests were conducted primarily with a sharp leading edge planar fin, although blunt and blunt swept planar fins were also used. The experimental data were used to develop new analytical and correlation procedures.
- Fluid Mechanics