SUPERSONIC WIND TUNNEL INVESTIGATION OF THE TURBULENT BOUNDARY LAYER ON AXIALLY SYMMETRIC BODIES.
UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES ENGINEERING CENTER
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This report describes a supersonic wind tunnel investigation of the turbulent boundary layer on three axially symmetric bodies at freestream Mach numbers of 1.61, 2.58, 3.30, and 4.50. Steady state temperature and pressure measurements were made in the boundary layers and on the surfaces of bodies that featured convex, concave, and bluntconvex-shouldered geometries, and transient temperature measurements were made on the surface of a convex-shouldered model that had been cooled with liquid nitrogen. Skin-friction measurements were also made with a floatingelement balance. Descriptions of the models, instrumentation and test program, and a discussion of the difficulties encountered in making some of the measurements are presented. Author