Accession Number : AD0818729

Title :   FULL SCALE SUBSONIC WIND TUNNEL TESTS ON FULLY EQUIPPED 75 AND 5 PERCENTILE DUMMIES.

Descriptive Note : Technical rept.,

Corporate Author : WEBER AIRCRAFT BURBANK CA

Personal Author(s) : Rickards, M. A. ; Collins, J. M.

Report Date : AUG 1967

Pagination or Media Count : 206

Abstract : Subsonic Wind Tunnel tests and correlative analyses were conducted at the Galcit 10 foot tunnel on fully equipped full-scale dummies in order to determine aerodynamic forces and moments acting on a crew member when fully immersed in the airstream. The dummy posture employed corresponds to tractor rocket personnel extraction from a disabled aircraft. In order to account for crew member size, a 75 percentile as well as a 5 percentile Sierra dummy was utilized. An F-105 survival kit was used during these tests. The tests involved a yaw range of 5 to 90 degrees, a pitch range of 0 to 360 degrees and any combination thereof. In addition, similar tests were conducted on a partial pitch range of 0 to 90 degrees without the survival kit. Body axes and wind axes are defined. Reference areas, lengths and center of gravity locations are cited as a function of percentile. The force and moment coefficients pertaining to both body and wind axes are presented in plotted and tabular form. Transfer equations between body and wind axes are formulated. Yaw-pitch angle correspondence for yaw angles exceeding 90 degrees are defined making six component aerodynamic data available for any angle of pitch and yaw involved in tumbling motion. (Author)

Descriptors :   *AERODYNAMIC LOADING), (*SUPERSONIC FLIGHT, EJECTION), (*ANATOMICAL MODELS, FLIGHT CREWS, AEROSPACE SYSTEMS, ESCAPE SYSTEMS, SURVIVAL KITS, SCALE, WIND TUNNEL MODELS, TUMBLING, POSTURE(PHYSIOLOGY), YAW, PITCH(MOTION), CENTER OF GRAVITY, MOMENTS, ROCKET PROPULSION, TOWED BODIES, MECHANICAL CABLES, EQUATIONS OF MOTION, TRANSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, TEST FACILITIES, SUSPENSION DEVICES, POSITIONING DEVICES(MACHINERY).

Subject Categories : Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE