Abstract
Based on the conformal transformation, a method for calculating the pressure distribution, the lift and the moment of a two-dimensional symmetrical airfoil executing unsteady motion in ideal fluid. The vortex sheet shed from the trailing edge is represented as the row of discretized vortices carried along with the fluid particles, assuming, for simplicity, that the amplitude of motion is very small and so the wake vortices lie on the real axis of the physical plane This method was applied to the symmetrical Joukowski airfoils with the thickness ratios of 6% to 30% and NACA 0012 airfoil, executing simple harmonic oscillation. The results show that the airfoil thickness effect tends to increase the amplitudes and the phase lags of the predicted aerodynamic forces.
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