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On the structure, interaction, and breakdown characteristics of slender wing vortices at subsonic, transonic, and supersonic speedsSlender wing vortex flows at subsonic, transonic, and supersonic speeds were investigated in a 6 x 6 ft wind tunnel. Test data obtained include off-body and surface flow visualizations, wing upper surface static pressure distributions, and six-component forces and moments. The results reveal the transition from the low-speed classical vortex regime to the transonic regime, beginning at a freestream Mach number of 0.60, where vortices coexist with shock waves. It is shown that the onset of core breakdown and the progression of core breakdown with the angle of attack were sensitive to the Mach number, and that the shock effects at transonic speeds were reduced by the interaction of the wing and the lead-edge extension (LEX) vortices. The vortex strengths and direct interaction of the wing and LEX cores (cores wrapping around each other) were found to diminish at transonic and supersonic speeds.
Document ID
19890063435
Document Type
Conference Paper
Authors
Erickson, Gary E. (NASA Langley Research Center Hampton, VA, United States)
Schreiner, John A. (NASA Ames Research Center Moffett Field, CA, United States)
Rogers, Lawrence W. (USAF, Wright Research and Development Center Wright-Patterson AFB, OH, United States)
Date Acquired
August 14, 2013
Publication Date
August 1, 1989
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 89-3345
Distribution Limits
Public
Copyright
Other