Accession Number : AD0696584

Title :   COMMUNICATION BETWEEN BASE AND LEEWARD REGION OF A CONE AT ANGLE OF ATTACK IN A 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 : 36

Abstract : The results of a wind tunnel investigation of separated flow over a 5.6 degree half-angle 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. It was observed that separated flow on the cone at angle of attack occurred while the cone leeward pressures were significantly larger than the base pressure. This large pressure difference indicated there was no subsonic communication between base and leeward region. The separated flow field for this case was then analogous to that of an infinitely long cone. At angles of attack greater than that which was required to equalize base and leeward pressures a new flow feature was observed. The cone leeward flow expanded to pressure levels below base pressure. A secondary separation occurred on the rear portion of the cone leeward surface, which appeared to contain subsonic reverse flow. In the neighborhood of this secondary separation, the leeward surface pressures increased and the separation line moved further away from the leeward meridian. (Author)

Descriptors :   (*REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), ATMOSPHERE ENTRY, FLOW SEPARATION, FLOW FIELDS, CONICAL BODIES, WIND TUNNEL MODELS, ANGLE OF ATTACK, VORTICES, THREE DIMENSIONAL FLOW

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE