S. Kleinveld, Q. Vinh Dinh, P. Ribaute, G. Rogè

For many industrial aircraft manufacturers, there is a real necessity to develop efficient optimization tools (for instance, optimization of aerodynamic shapes) in order to reduce the design period of new planes with an increased configuration complexity. The present paper discusses the results of aerodynamic shape optimization on a full aircraft geometry, including wings, body and nacelle of a Dassault generic business jet. This test case configuration study was computed in the transonic domain. We consider a classical shape optimization problem subject to the compressible Euler flow equations. The gradient of the cost functional with respect to the shape variables is derived with the adjoint method at the discrete level. As the main features of this work we can list the following keywords: unstructured meshes, discrete sensibilities, exact adjoint, CAD modeler.

CEAS Conference on Multidisciplinary Aircraft Design and Optimization; Köln; 2001

Book Chapter

englisch

14,8 x 21,0 cm, 10 Seiten

DGLR-Bericht, 2001, 2001-05, CEAS Conference on Multidisciplinary Aircraft Design and Optimization; S.249-258; 2001; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, computational fluid dynamics, computer aided design, aeronautics, multidisciplinary design optimisation

Bestellbar

2001