Accession Number : AD0263083

Title :   THE LAMINAR BOUNDARY LAYER AT HYPERSONIC SPEEDS

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : FERRARI,CARLO

Report Date : SEP 1961

Pagination or Media Count : 1

Abstract : A theoretical inquiry is made into the nature of the laminar boundary layer on an airfoil immersed in a hypersonic stream under the assumptions that: (a) there is no hea trans er to the wall and the Prandtl number is unity and (b) there is a zero gradient of pressure normal to the direction of development of the layer along the wall. In the derivations, the treatment will be strictly applicable only at a sufficient distance downstream rom the leading edge. On the basis of the results ded ced from such an analysis, it becomes clear that the influence of the pressure gradient, created by the presence of the thick boundary layer, is appreciable even when the hypersonic similarity parameter is as low as 0.12. (Author)

Descriptors :   *AIRFOILS, *HYPERSONIC CHARACTERISTICS, *HYPERSONIC FLOW, *LAMINAR BOUNDARY LAYER, DEFLECTION, GAS FLOW, HEAT TRANSFER, INTEGRAL EQUATIONS, MATHEMATICAL ANALYSIS, PARTIAL DIFFERENTIAL EQUATIONS, PRESSURE

Distribution Statement : APPROVED FOR PUBLIC RELEASE