A Study of Flow Separation in Regions of Shock Wave-Boundary Layer Interaction in Hypersonic Flow.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1975
- Accession Number
- ADA015061
Entities
People
- Michael S. Holden
Organizations
- New York University