Transition of a Supersonic Boundary Layer Over an Unswept Wing Due to Acoustic Noise.

In this paper, we present the results of direct numerical modeling of the process of susceptibility of a supersonic boundary layer over an unswept wing with a thin parabolic profile to acoustic noise of various intensities. It was demonstrated that acoustic noise can cause a laminar–turbulent transition over the unswept wing of a supersonic passenger aircraft. [ABSTRACT FROM AUTHOR]