Abstract: An inverse design method of transonic airfoil and wing is described, in which following modification are made for improving convergence and extending application areas: an artificial viscosity term is added to increase the ability of dealing with the shock; a Riegels type of leading edge correction is taken to remove the singularity at the leading edge of the round-nosed airfoil; a smoothing-relaxation procedure is proposed; all coefficients in the equations are integrated in analytical form. A regularity condition in closed form for the transonic airfoil design is presented. A few design results indicate that this method is effective in the transonic airfoil and wing design.

Key words: transonic flow, airfoils, wings, design