Abstract

An inverse computational method for transonic airfoil and wing design is presented. Improvements aimed at increasing abilities of the method and computational efficiency have been taken. For example, a Riegels type leading edge correction is introduced. An artificial viscosity term is added to the integral equation method and a smoothing-relaxation procedure is proposed. In 2D transonic flow case, a regularity condition in closed form to be satisfied by a target pressure distribution is used. A few given design results illustrate that the present method is an efficient tool for transonic airfoil and wing design.

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