Abstract
An inverse, transonic flow method for the design of three-dimensi onal wings has been developed. The flow method is based on a three-dimensional, finite-differ ence solution of the full-potential equation. The inverse scheme utilizes a Dirichlet boundary condition in conjunction with surface transpiration to affect geometry definition. Such a scheme has previously been utilized in a two-dimensional method. This paper summarizes an analogous development for three dimensions. Basic steps and underlying assumptions of the inverse scheme are described. Applications of the method to both simple and complicated design problems are discussed and advantages of the method are identified.
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