Accession Number:

AD0631477

Title:

RAREFACTION EFFECTS ON IMPACT PRESSURE PROBES IN HYPERSONIC FLOW,

Descriptive Note:

Corporate Author:

AEROSPACE RESEARCH LABS OFFICE OF AEROSPACE RESEARCH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1965-09-01

Pagination or Media Count:

35.0

Abstract:

An experimental investigation of impact pressure behavior was conducted at elevated hypersonic Mach numbers and low Reynolds numbers. The results clearly indicated a Mach number dependence of the impact pressure characteristics. It was demonstrated that at constant Reynolds number, the impact pressure ratio increases systematically with increasing Mach number in the fully merged flow regime. It was found that no single parameter would adequately correlate the data throughout the complete range of test conditions. However, verification of the existence of a hypersonic similarity parameter for the blunt body was demonstrated over the test Reynolds number range of 50 to 350. A qualitative explanation of the observed pressure behavior has been suggested based on an assumed physical model. It appears that the continuum approach to theoretical blunt body flows could be further extended into the rarefied flow regime through proper analytical treatment of the rarefaction effects on the bow shock wave. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE