AN INVERSE DESIGN METHOD OF TRANSONIC AIRFOIL AND WING

An inverse design method of transonic airfoil and wing is described, in which the followingmodifications are made for improving convergence and increasing application ability:an artificial viscosity term is added to the integral equation method to increase the abilityof dealing with the shock; a Riegels type of leading edge correction is taken to removethe singularity at the leading edge of the round-nosed airfoil; a smoothing-relaxation procedureis proposed; all coefficients in the equations are integrated in the analytical form. Aregularity condition in closed form for the transonic airfoils is presented. A few design resultsindicate that this method is effective in the transonic airfoil and wing design.