A 'pylon vortex generator' concept has been proposed for alleviating the subsonic pitch-up instability of highly swept supersonic-cruise wings. Fixed at a part-span location, this leading-edge device utilizes the lateral velocity component in the flow approaching the swept leading edge to generate a streamwise vortex, opposite in sense to the tip vortex. The vortex-induced downwash outboard of the device serves to control the leading-edge stall development in the wing-tip regions. Wind-tunnel results on 60-deg and 74-deg flat-plate delta wings are presented to illustrate the operation of the pylon vortex generator in modifying the spanwise leading-edge separation characteristics resulting in effective alleviation of the pitch-up.
Alleviation of the subsonic pitch-up of delta wings
Aerospace Sciences Meeting ; 1982 ; Orlando, FL
01.01.1982
Aufsatz (Konferenz)
Keine Angabe
Englisch
Alleviation of the subsonic pitch-up of delta wings
AIAA | 1983
|Alleviation of the subsonic pitch-up of delta wings
AIAA | 1982
|Subsonic pitch-up alleviation on a 74 deg delta wing
NTRS | 1981
|Alleviation of pitch-up on delta wings using distributed porosity
Online Contents | 1999
|Subsonic wing rock of slender delta wings
AIAA | 1985
|