Accession Number : AD0466166


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


Corporate Author : ARO INC ARNOLD AFS TN


Personal Author(s) : Ray, A D ; Palko, R L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/466166.pdf


Report Date : Jul 1965


Pagination or Media Count : 26


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.


Descriptors :   *BLUNT BODIES , AERODYNAMIC HEATING , ANGLE OF ATTACK , BOUNDARY LAYER , DISTRIBUTION , EXPERIMENTAL DATA , GRAPHICS , HEAT TRANSFER , HEAT TRANSFER COEFFICIENTS , HYPERSONIC CHARACTERISTICS , HYPERSONIC FLOW , MODEL TESTS , PRESSURE , REYNOLDS NUMBER , SEPARATION , SHOCK WAVES , SPARK SHADOWGRAPH PHOTOGRAPHY , SWEPTBACK WINGS , TEMPERATURE , WIND TUNNEL MODELS


Subject Categories : Theoretical Mathematics


Distribution Statement : APPROVED FOR PUBLIC RELEASE