Canard-wing vortex interactions at subsonic through supersonic speedsThe NASA-Ames 6 x 6-foot Transonic/Supersonic Wind Tunnel has been used to conduct a study of canard-wing flowfield interactions at sub-, trans-, and supersonic speeds, giving attention to vortex interactions, vortex breakdown, shock-wave development, and vortex-shock interactions. The results obtained show that the canard-wing flowfield interaction delays vortex breakdown to a higher angle-of-attack at sub- and transonic speeds; while the flowfield interference eliminates shock-induced secondary boundary layer separation on the wing, it does not alter the location and development of a rear shock wave extending laterally across the wing. A canard-induced upwash field accelerates the upward migration of the wing vortex at sub-through-supersonic speeds, but is most pronounced at transonic speeds due to the interaction of the vortical flow with the rear shock wave.
Document ID
19900058099
Acquisition Source
Legacy CDMS
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)