The present study presents a new nonlinear unsteady aerodynamic model to investigate the aeroelastic behavior of a self-sustained oscillating rigid airfoil.Here the unsteady Euler equations are considered to simulate inviscid compressible transonic flow over an oscillating airfoil. In respect to provide boundedness criteria, a high-order technique based on a normalized variable diagram (NVD) scheme has been presented. Unlike the application of a dynamic mesh which is too complex to implement and that requires a lot of computational efforts, the current paper propose a non-orthogonal and static mesh with oscillation of flow boundary.The unsteady flow results for the airfoil pitching and plunging are compared with both well-validated numerical methods and experimental data. A time-marching method is employed to determine system responses. The predicted flutter boundary for NACA0012 airfoil at different free stream Mach numbers is in fair agreement with direct flutter tools of the Hopf bifurcation points. Finally, the influences of the center of mass and elastic axis position on the system aeroelastic behavior are examined.

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