Accession Number : ADA132159

Title :   A Preliminary Windtunnel Investigation of a Wing Tip Static Pressure Amplification Device,

Corporate Author : PRINCETON UNIV N J DEPT OF AEROSPACE AND MECHANICAL SCIENCES

Personal Author(s) : Hazen,D C

PDF Url : ADA132159

Report Date : Oct 1974

Pagination or Media Count : 27

Abstract : A series of windtunnel investigations of a model utilizing a variety of ducted wing tip sections was conducted in the Princeton University 4' x 5' windtunnel during September and October 1974. The ducted section consisted of a venturi entry portion that could be tested with a number of different discharge slots of various geometries. The tests showed that significant amplification of the free stream static pressure could be achieved; that in general the magnitude of the amplification factor decreased with angle of attack; the magnitude of the factor could be significantly affected by the location and shape of the exit slot; and that the nature of the resulting signal was influenced by the location of the entry slot with relation to the leading edge.

Descriptors :   *Wing tips, *Wind tunnel tests, Static pressure, Free stream, Amplification, Ducts, Slots, Leading edges, Angle of attack

Subject Categories : Aircraft
      Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE