| Abstract: | In this paper, on the basis of the variational principles developed the finite element method (FEM) is employed for numerical solution of the inverse pro blem of 2 D unsteady compressible flow around oscillating airfoils by incorporating the non reflecting far field boundary conditions and a new unsteady Kutta condition. All unknown boundary (airfoil contour) and discontinuities(shocks and free trailing vortex sheets) are determined via the functional variation with variable domain and artificial density concept. For the numerical realization of the variable domain variation, a special finite element with self adjusting nodes is also suggested herein. The numerical results show that the present method is effective for the design of unsteady airfoil. |
