Receptivity of a swept-wing boundary layer to steady vortical free-stream disturbances

Abstract

Direct numerical simulations (DNS) of steady vortical free-stream disturbances impinging on the leading edge of a swept wing are performed for a lowand a high-speed subsonic case at a Mach number of 0.16 and 0.65, respectively. The receptivity of the crossflow-instability dominated boundary layer downstream of the stagnation line to the forced disturbances is investigated. The introduced (spanwise) wavelengths are in the order of the most amplified steady crossflow mode in the low Mach-number case and induce respective low-amplitude disturbances in the boundary layer.