Abstract
A direct numerical optimization methodology combining nonlinear programming and approximation concepts is studied in the context of CFD-based engine/airframe integration. It aims at reducing the number of full CFD analyses required in the course of an optimization, by replacing the original optimization problem by a set of approximate problems, thus reducing computational cost considerably. The performance of global local approximations (GLA) is tested and compared to that of a more common first-order Taylor series approximation. These approximations are obtained with alternative simplified aerodynamic analysis techniques corrected by CFD computations. A two-dimensiona l NASP-like configuration serves as a test case. In this article the basic procedure is reviewed and results based on optimization studies of the nozzle and forebody are presented. Problems associated with the application of GLA to CFD-based optimization are discussed and some solutions and insights are provided. Nomenclature flcurvc = curvature
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