Accession Number : AD0737507
Title : Shock Impingement Caused by Boundary Layer Separation Ahead of Blunt Fins.
Descriptive Note : Research memo.,
Corporate Author : GRUMMAN AEROSPACE CORP BETHPAGE N Y RESEARCH DEPT
Personal Author(s) : Kaufman,Louis G. , II ; Korkegi,Robert H. ; Morton,Leo C.
Report Date : FEB 1972
Pagination or Media Count : 22
Abstract : High speed flow past a blunt protuberance on a surface results in a complex, three dimensional, inviscid-viscous interaction flow field. Characteristically, the interaction results in a separated flow region composed of horseshoe vortices near the surface, and a lambda-type shock pattern in the plane of symmetry ahead of the protuberance. The shock wave emanating from the separated flow region impinges on the bow shock ahead of the protuberance and causes intense heating and high pressures locally on the protuberance leading edge. The heating and pressure in this local area can be 10 times larger than the undisturbed stagnation line values; the amplification depends strongly on local flow conditions. Tests were conducted to examine and obtain a better understanding of these interaction flow fields; the most recent tests included detailed flow field surveys for Mach 3 flows ahead of blunt fins on a flat plate surface with turbulent boundary layers. (Author)
Descriptors : (*FINS, *BOUNDARY LAYER TRANSITION), SHOCK WAVES, BLUNT BODIES, FLOW SEPARATION, FLOW FIELDS
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE