Accession Number : ADA184636

Title :   An Investigation of the Parallel Blade-Vortex Interaction in a Low-Speed Wind Tunnel,

Corporate Author : TEXAS UNIV AT ARLINGTON DEPT OF AEROSPACE ENGINEERING

Personal Author(s) : Seath,Donald D. ; Kim,Jai-Moo ; Wilson,Donald R.

Report Date : 10 JUN 1987

Pagination or Media Count : 12

Abstract : Low-speed wind tunnel tests were conducted to investigate the parallel blade-vortex interaction. Flow visualization tests of vortex generation performed prior to the pressure tests showed that a well defined starting vortex was generated by an impulsively pitched wing. Time history of the pressure distribution on a pressure-tapped wing model was acquired as the starting vortex passed over the wing. These pressure tests revealed that a substantial pressure change near the leading edge was induced by the encountering vortex. The effects of vortex proximity reduced frequency and maximum pitch angle of the vortex generator on the pressure change were also investigated.

Descriptors :   *ROTOR BLADES(ROTARY WINGS), *VORTICES, INTERACTIONS, FLOW VISUALIZATION, VORTEX SHEDDING, WIND TUNNEL TESTS, HOVERING, PRESSURE DISTRIBUTION, HELICOPTER ROTORS

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE