Accession Number:

AD0466166

Title:

AN INVESTIGATION OF THE EFFECTS OF SHOCK IMPINGEMENT ON A BLUNT LEADING EDGE

Descriptive Note:

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1965-07-01

Pagination or Media Count:

26.0

Abstract:

Tests were conducted at hypersonic Mach numbers on a blunt leading edge model both with and without an impinging shock. The effects of Reynolds number, Mach number, leading edge sweep angle, and impinging shock strength on the temperature and pressure distribution for the leading edge were determined. The tests were conducted at nominal Mach numbers of 6, 8, and 10 unit Reynolds numbers of 580,000 to 3,550,000 per foot with a sweep angle range of 0 to 75 deg. Selected results which show the effect of shock generator angle and sweep angle at Mach 6 and 10 are presented.

Subject Categories:

  • Theoretical Mathematics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE