Analysis of Vortex Burst Phenomena on Generic Hybrid Delta Wing Planforms at Subsonic Speeds

Abstract

In this study, experimental investigations are performed to analyze the vortex behavior and breakdown characteristics on a generic multiple swept wing fuselage configuration. Fast Response Aerodynamic Pressure Probe and Particle Image Velocimetry measurements are performed in the low-speed wind tunnel W/T-A facility of the Chair of Aerodynamics and Fluid Mechanics at the Technical University of Munich. The experiments are executed at subsonic speed, symmetric freestream conditions and angles of attack of \\(\\alpha = 16^\\circ , 24^\\circ \\) and \\(32^\\circ \\). In a power spectral density analysis of velocity fluctuations helical mode instabilities and shear layer instabilities can be detected.