Accession Number : AD0760807

Title :   Asymmetric Nose Bluntness Effect on the Aerodynamics of a Slender Cone at Mach-14,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Walchner,Otto

Report Date : APR 1973

Pagination or Media Count : 32

Abstract : Experiments were performed in ARL's 20-inch hypersonic wind tunnel on a 10 degree half-angle circular cone model whose pointed tip was removed by one or more planar slanted cuts. The projected frontal nose area was 1/2 percent of the base area. The configurational asymmetry of this moderate bluntness destroys the rotational symmetry of the shock wave over the entire model. In turn, the rotational symmetry of the surface pressure distribution is also lost. Depending on the nose configuration, asymmetric sideloads were observed at axial flow conditions which may or may not cause the vehicle to trim in free flight. Nose asymmetry combined with mass asymmetry, therefore, may produce a rolling moment even at zero trim. The stability derivatives are not identical in pitch and yaw, as would be expected for a body of revolution, and vary differently as functions of the angle of attack and angle of sideslip. (Modified author abstract)

Descriptors :   (*REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), CONICAL BODIES, ANGLE OF ATTACK, PITCH(MOTION), YAW, PRESSURE, FLOW VISUALIZATION, SLENDER BODIES

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Guided Missile Reentry Vehicles

Distribution Statement : APPROVED FOR PUBLIC RELEASE