Accession Number : AD0720661

Title :   Hypersonic Laminar Boundary-Layer Separation on a Slender Cone at Angle of Attack,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Stetson,Kenneth F. ; Ojdana,Edward S.

Report Date : 1971

Pagination or Media Count : 23

Abstract : Wind tunnel experiments with a 5.6 degree half angle cone at M = 14.2 indicated that the three-dimensional separation bubble concept was not the correct flow field model for these data. Based upon data consisting of surface pressure measurements, pitot pressure surveys, and surface oil flow patterns a new model for hypersonic three-dimensional separation is proposed. This model contains symmetrical supersonic helical vortices with an attachment line on the most leeward ray. The vortices are in contact with the surface, at least up to 18 deg angle of attack, and there is no subsonic reverse flow or singular points associated with the vortex pattern. (Author)

Descriptors :   (*REENTRY VEHICLES, *FLOW SEPARATION), HYPERSONIC CHARACTERISTICS, WIND TUNNEL MODELS, BOUNDARY LAYER, THREE DIMENSIONAL FLOW, SLENDER BODIES, ANGLE OF ATTACK, VORTICES, BLUNT BODIES

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE