Accession Number : AD0716336

Title :   An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part I. A Detailed Description of the Experiment and Data Tabulation,

Corporate Author : BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD

Personal Author(s) : Sturek,Walter B.

Report Date : OCT 1970

Pagination or Media Count : 129

Abstract : Experimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of zero pressure gradient and 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 taken through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made in a supersonic wind tunnel for a nominal tunnel nozzle setting of Mach 3.5. The data are for an adiabatic wall with values of momentum thickness Reynolds number ranging from 19,000 to 42,000. The experiment is described in detail and the mean profile data are presented in tabular form. Fluctuation data obtained using constant temperature hot wire anemometry are presented for one station in the region of zero pressure gradient and for one station in the region of adverse pressure gradient. (Author)

Descriptors :   (*TURBULENT BOUNDARY LAYER, *SUPERSONIC CHARACTERISTICS), PRESSURE, AIRFOILS, THICKNESS, CURVED PROFILES, FLOW VISUALIZATION, STATISTICAL DATA

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE