Experimental Study of Shock Impingement on a Blunt Leading Edge with Application to Hypersonic Inlet Design.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1971
- Accession Number
- AD0726111
Entities
People
- Paul J. Ortwerth
- Roger R. Craig
Organizations
- Air Force Research Laboratory