Accession Number : ADA015061

Title :   A Study of Flow Separation in Regions of Shock Wave-Boundary Layer Interaction in Hypersonic Flow.

Descriptive Note : Final rept. 1 Sep 72-31 May 74,

Corporate Author : NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB

Personal Author(s) : Holden,Michael S.

Report Date : JUN 1975

Pagination or Media Count : 53

Abstract : This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.

Descriptors :   *Flow separation, *Boundary layer flow, *Hypersonic characteristics, Reynolds number, Shock tunnels, Test methods, Flat plate models, Viscous flow, Heat transfer, Pressure, Interactions, Laminar boundary layer, Wedges, Compressive properties, Theory, Attachment

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE