Direct numerical simulations (DNS) of steady controlled free-stream disturbances impinging on a swept-wing leading edge are performed for a low- and a high-speed subsonic case at a Mach number of 0.16 and 0.65, respectively. The former represents generic wind-tunnel conditions, the latter is comparable to transonic free flight. The receptivity of the crossflow-instability dominated boundary layer on the upper wing side to the oncoming disturbances is investigated. The spanwise wavelengths of the forced disturbances are adjusted to induce amplified crossflow modes in both the low-speed and the high-speed case.
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