A. Dugeai

This paper presents the numerical tools which have been developped at ONERA s structural division in order to calculate generalized aerodynamic forces for supersonic aircrafts. A new method is described which is able to calculate aerodynamic forces for bodies following supersonic linearized theory. This method is a mixed finite elements - integral equation method whose main features are identical in the steady and in the unsteady cases. The Greens formulation of the linearized problem is treated in a variationnal way, and it is projected in an approximation space where the unknowns are the values of the potential at each node of a triangular mesh approximating the surface of the body. The resolution of a linear system allows to calculate the aerodynamic forces. Several examples are shown and they are compared to other methods or experimental data, either in the steady case or the unsteady case.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.43-53; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991