Experimental study of the vortex flow behavior on a generic fighter wing at subsonic and transonic speedsA subsonic and transonic investigation of the vortex flow behavior of a generic fighter configuration with 55-deg cropped delta wing has been conducted in order to improve current understanding of vortical motions on a wing with deflected leading edge flap at moderate and high angles-of-attack. The leading edge vortex strength was reduced, and the vortex was flatter and closer to the wing surface, as the Mach number increased. Transonically, at high angles-of-attack, the test data suggested the development of a cross-flow shock wave above the vortex sheet which coexisted with a rear shock wave. Subsonically, a deflected leading edge flap was able to sustain a concentrated vortex on the forward-facing surface.
Document ID
19870057646
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Erickson, Gary E. (NASA Ames Research Center Moffett Field, CA, United States)
Rogers, Lawrence W. (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB OH, United States)