Supersonic Turbulent Boundary Layer in Adverse Pressure Gradient. Part I: The Experiment

Abstract

Experimental measurements of the mean profile characteristics of the supersonic turbulent boundary layer in a region of moderate adverse pressure gradient along the curved surface of an isentropic ramp model are reported. Detailed surveys of impact pressure, static pressure and total temperature were made through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made for a nominal tunnel nozzle setting of Mach 3.5, closely adiabatic wall, and momentum thickness Reynolds number of 1.9 to 4.2 x 10. In addition to the mean profile data, fluctuation data were obtained using constant temperature hot wire anemometry at one station in the region of zero pressure gradient and at one station in the region of adverse pressure gradient.