Accession Number : AD0268584

Title :   COMPRESSIBLE BOUNDARY LAYER EQUATIONS AND STAGNATION POINT SOLUTION WITH DIFFERENCES IN THERMAL AND DYNAMIC BOUNDARY LAYER THICKNESSES BEING CONSIDERED

Corporate Author : AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OHIO FLIGHT CONTROL LAB

Personal Author(s) : BUCK,MELVING L.

Report Date : AUG 1961

Pagination or Media Count : 1

Abstract : This analysis is the groundwork for presenting boundary layer characteristics as functions of universal parameters. The usual assumption, that the thermal and dynamic boundary layer thicknesses have negligible effect on the boundary layer characteristics, is analyzed. Compressible laminar boundary layer equations with arbitrary pressure and temperature gradients are solved for stagnation point. The solution considers the difference in thermal and dynamic boundary layer thicknesses. Computations were carried out for stagnation point flow using this analysis. The analysis shows that the difference in thermal and dynamic layers has an appreciable effect on the heat transfer paarameter and a secondary effect on the skin friction parameter and the other characteristics of the boundary layer. The analysis indicates that the effect of the difference in the thermal and dynamic layers should be considered in any analysis of the boundary layer. (Author)

Descriptors :   *BOUNDARY LAYER, *LAMINAR BOUNDARY LAYER, FLUID FLOW, FLUID MECHANICS, FRICTION, GASES, HEAT TRANSFER, HOUSING(DWELLINGS), HYPERSONIC CHARACTERISTICS, SUPERSONIC FLOW, SURFACE PROPERTIES, TEMPERATURE, THERMAL DIFFUSION

Distribution Statement : APPROVED FOR PUBLIC RELEASE