Abstract: People hope that aircraft shape can adjust according to the change of flow condition, thus it is essential to learn about the unsteady aerodynamic phenomenon and mechanism of deformable aircrafts. Then the deformation vehicle performance can be improved, and the safety of flight can be ensured. In this paper, supercritical airfoil was focused on, and airfoil thickness and camber deformation schemes were designed, respectively. Numerical simulation method was used to simulate the unsteady effect due to the airfoil thickness or camber deformed in high Reynolds number condition. The results show that the unsteady effect is strong with distinguishable lift and drag hysteresis loops. In addition, as the deformation frequency and amplitude increase, the unsteady effects are significantly strengthened. The unsteady effect resulted from the camber deformation is relatively stronger than that from the thickness deformation. Finally, by analysing the flow streamline and pressure coefficient distribution, the unsteady effects with geometric distortion can be produced by the hysteresis of the flow structure, such as the strength and location of shock, and the boundary layer separation.