Stability of the Boundary Layer on a Swept Wing with Wall Cooling Spyridon

Linear stability theory was used to examine the propagation of laminar instabilities in the leading edge region of a transonic swept wing with wall cooling. The condition of real group velocity ratio on the eigenvalue computation was examined for the case of crossflow instabilities. When temporal theory was used, this condition resulted in a single wave of maximum amplification. When spatial theory was used, and for a limited range of angles of wavegrowth direction, the growth rate in the direction formed by the real ratio of the group velocities and the direction itself were insensitive to the orientation of the wavegrowth. It was found that wall cooling has a stabilizing effect on crossflow disturbances, but the stabilization is mild compared to the stabilizing effect that wall cooling has on Tollmien-Schlichting waves.