Accession Number : AD0729325

Title :   An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part II. Analysis of the Experimental Data,

Corporate Author : BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD

Personal Author(s) : Sturek,W. B.

Report Date : JUN 1971

Pagination or Media Count : 58

Abstract : The experimental data reported in Part 1 are analyzed. Turbulent boundary layer equations applicable to compressible flow over a surface with longitudinal curvature are evaluated by numerical integration using the tabulated profile data. Curvature corrections to the equation for conservation of streamwise momentum are shown to be small but of the same order of magnitude as the wall shear stress. The data are shown to correlate in law of the wall and velocity defect dimensionless coordinates using an integral compressibility transformation. Values of skin friction coefficient calculated using the experimental data are compared to other experimental data and to values predicted using the Spalding-Chi method. (Author)

Descriptors :   (*TURBULENT BOUNDARY LAYER, SUPERSONIC CHARACTERISTICS), (*CURVED PROFILES, TURBULENT BOUNDARY LAYER), EXPERIMENTAL DATA, EQUATIONS OF MOTION, AIRFOILS, PRESSURE, SKIN FRICTION, NUMERICAL METHODS AND PROCEDURES, MATHEMATICAL PREDICTION

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE