Abstract
An iterative Inverse Design System is presented for the aerodynamic design of isolated and wing-mounted engine nacelles. The flow solver used is the DLR Tau code, a finite-volume flow solver for the solution of the Reynolds-Averaged Navier-Stokes equations on arbitrary grids. The inverse design method is based on an iterative residual-correction type approach and attempts to generate a geometry which satisfies a user-prescribed target pressure distribution. Results are presented for the inverse design of isolated and wing-mounted engine nacelles under consideration of the pylon.
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