3D transonic nacelle and winglet design

This paper discusses the application of a predictor/corrector design method originally developed at the NASA Langley Research Center. The ability to couple the predictor/corrector method to existing CFD analysis tools (or flow solvers) gives promise of a design technology that can be applied to a variety of practical aerodynamic engineering problems. This paper will describe some of the initial experiences of adapting the NASA predictor/corrector design method, which include its application to the design of the fan cowl of a turbofan engine and to the design of a partial chord winglet.