Accession Number : AD0732890

Title :   Base Pressure on a Sting-Mounted Cone Model at Angle of Attack at M(Infinity) Equals 14.2.

Descriptive Note : Final rept.,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

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

Report Date : AUG 1971

Pagination or Media Count : 35

Abstract : Wind tunnel oil flow experiments on a sharp cone model at free stream Mach number = 14.2 revealed that flow attachment on the sting changed considerably with angle of attack. A flow pattern developed which contained two stagnation regions, one on the leeward meridian and one on the windward meridian. The cross-flow about the sting separated at angles of attack as low as four degrees. The cone base pressures in the leeward region remained essentially constant with increases in angle of attack, whereas the windward region pressures decreased. (Author)

Descriptors :   (*REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), FLOW SEPARATION, WIND TUNNEL MODELS, FLOW VISUALIZATION, MODEL TESTS, STAGNATION POINT, ANGLE OF ATTACK, FLOW FIELDS

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE