Flow Pattern of Compressible Convex-Corner Flow

What is it about?

The design for a transonic wing using variable camber depends on the extent of the supersonic region, the pressure gradients in the recompression zone and the surface curvature. For a fixed wing, a variable camber configuration increases lift-to-drag ratio. However, the deflection of control surfaces on a transonic wing can initiate boundary layer separation which is associated with the drag divergence Mach number. This study determines the flow pattern for a convex corner which can be used to represent the upper surface of a deflected control surface.

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