Accession Number : AD0696583
Title : SURFACE CONDITIONS IN THE LEEWARD REGION OF A BLUNT CONE AT ANGLE OF ATTACK IN HYPERSONIC FLOW.
Descriptive Note : Final rept.,
Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
Personal Author(s) : Stetson,Kenneth F. ; Friberg,Eric G.
Report Date : JUL 1969
Pagination or Media Count : 44
Abstract : The results of a wind tunnel investigation of separated flow over a blunt cone at angle of attack are presented. Surface pressure and oil flow data were obtained at a free stream Mach number of 14.2 and a free stream Reynolds number per foot of 650,000. A three-dimensional separation model for hypersonic flow over a blunt cone at angle of attack is proposed. The leeward side of the cone contains an initial region of attached, converging flow followed by a divergence into the separated region. The separated region does not originate from a singular point on the leeward meridian. In place of the expected singular point was a 'neck' through which fluid passed from the upstream attached flow region into the separated region. Symmetrical separation lines developed downstream of the neck as the surface streamlines diverged. There was no evidence of reverse flow or subsonic communication with the base region. The separated region was considered to have the characteristics of symmetrical supersonic helical vortices. (Author)
Descriptors : (*REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), ATMOSPHERE ENTRY, BLUNT BODIES, CONICAL BODIES, WIND TUNNEL MODELS, PLASMA SHEATHS, FLOW SEPARATION, THREE DIMENSIONAL FLOW, ANGLE OF ATTACK, VORTICES
Subject Categories : Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE