Iterative three-dimensional transonic wing design using integral equations

A practical design method is presented for three-dimensional transonic wings with prescribed pressure distributions. The method is based on an iterative residual-correction concept. The residual, defined as the difference between the computed and the prescribed pressure distributions at each iteration step, is determined by the use of an existing direct analysis code for a transonic wing with or without the body. The wing geometry correction to compensate for the residual can be approximately obtained from the inverse solution code developed in the present study. The inverse (correction) problem is mathematically reduced to a Dirichlet boundary value problem that is solved here by the aid of the transonic integral equation method. Some of the design results are also presented for transonic swept wings.