Dynamic Stall Control by Variable Airfoil Camber

In the present numerical investigations the unsteady flow about a helicopter airfoil section under deep dynamic stall conditions has been influenced by dynamic airfoil deformation. First attempts with a dynamic stall phenomenon: the dynamic stall onset could be shifted to considerably higher incidences within the oscillatory loop. In the present paper the extension of this method to more arbitrary types of dynamic deformations is discussed and the influence of a dynamic change of the airfoil leading edge curvature (nose droop) is investigated in detail. Special emphasis is placed on the variation of the Machnumber