Numerical investigation of laminar separated trailing-edge flows

An efficient time-marching numerical method has been developed for solving problems involving supersonic laminar separated trailing-edge flows using a triple-deck formulation. The accuracy of the numerical method was tested for the case of a flat plate embedded in a supersonic flow at angles of incidence below stall. A range of numerical solutions is presented for angles of incidence beyond stall in the form of streamline and shear contour plots. The trailing-edge shear on the side of the plate where separation occurs reaches an asymptotic value as the angle of incidence is increased; beyond this point numerical instability was encountered.