Accession Number : AD0765164

Title :   'In-Plane' and 'Out of Plane' Stability Derivatives of Slender Cones at Mach 14,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Walchner,Otto ; Sawyer,Frank M.

Report Date : JUL 1973

Pagination or Media Count : 27

Abstract : A 10-deg. circular cone with various spherical and conical (45 degrees) nose bluntnesses of 1.7%, 10% and 25% was investigated in ARL's Mach-14 wind tunnel. Test results confirm that the static and dynamic stability coefficients are not equal in pitch and in yaw for nonzero angles of attack if the pitching moment becomes a nonlinear function of angle of attack due to nose flunting. The inequality of the in plane and out of plane stability derivatives was found at small angles of attack which are only fractions of the cone half angle. (Author)

Descriptors :   (*REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), CONICAL BODIES, WIND TUNNEL MODELS, ANGLE OF ATTACK, STABILITY, PITCH(MOTION), YAW

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

Distribution Statement : APPROVED FOR PUBLIC RELEASE