Accession Number:

AD0749946

Title:

Interference Heating Due to Shock Impingement

Descriptive Note:

Final rept. May 1971-Jul 1972

Corporate Author:

GRUMMAN AEROSPACE CORP BETHPAGE NY

Report Date:

1972-07-01

Pagination or Media Count:

178.0

Abstract:

Investigation of the interference heating phenomenon was conducted at Mach number 8 over a Reynolds number range from 400 thousand to 3.7 million per ft in the hypersonic wind tunnel. Shock generator models consisted of 1.5, 5, 10 and 15 deg wedges 2.5, 7.5 and 12.5 deg cones .5 and 2.0 in. diameter hemispheres, and an orbiter-type vehicle. Shock receiver models included sharp and blunt flat plates and a booster vehicle. Both pressure distributions and heat transfer distributions were obtained in the regions of shock impingement. The test program was organized in a building-block approach. A limited number of sharp plate runs were performed with a boundary layer trip to obtain turbulent data for comparison with other experiments.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE