Accession Number : AD0726111
Title : Experimental Study of Shock Impingement on a Blunt Leading Edge with Application to Hypersonic Inlet Design.
Descriptive Note : Technical rept. Dec 67-Mar 69,
Corporate Author : AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
Personal Author(s) : Craig,Roger R. ; Ortwerth,Paul J.
Report Date : APR 1971
Pagination or Media Count : 43
Abstract : An experimental study was made of the interaction of an oblique shock with the bow shock of blunt leading edge. The interactions were classified according to the interference patterns described by Edney. Peak heating rates 5.5 times those of the blunt leading edge alone were studied. All interactions appeared to be unsteady except when the slipstream of the interaction passed above the blunt leading edge. (Author)
Descriptors : (*RAMJET INLETS, SHOCK WAVES), HYPERSONIC CHARACTERISTICS, BLUNT BODIES, LEADING EDGES, WIND TUNNEL MODELS, MODEL TESTS, HEAT TRANSFER, PRESSURE
Subject Categories : Aerodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE