In the present research the effect of flexible shells method in unsteady viscous flow around airfoil have been studied. In the presented algorithm due to the interaction of the aerodynamic forces and the structural stiffness (FSI) a geometrical deformation as bump is created in the area where the shock occurs.This bump causes instead of compressive waves, a series of expansion waves that produce less drag and also improves the aerodynamic performance be formed. The main goal is to reduce wave drag throughout the flight range. By using this method we can be more effective than recent methods in throughout the flight because if there is a shock, a bump will form in that area and if the shock does not occur, the shape of the airfoil will not change.

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