The computation of transonic airfoil and wing design
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.
KeywordsPressure Distribution Integral Equation Method Artificial Viscosity Aerodynamic Design Wing Design
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