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):

Report Date:

1971-04-01

Pagination or Media Count:

43.0

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

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE