G.D. Mortchelewitcz, A.S. Sens

A numerical method has been developed at ONERA in order to study the transonic aeroelastic properties of aircraft. The 3-D unsteady Euler equations are solved using unstructured meshes made up of tetrahedra. In this context, the finite element method is used to construct the space of approximation. The flow solver involves an explicit-implicit scheme with implicit equations to be solved approximately using two Jacobi iterations. With this solver, artificial viscosity is added explicitly to prevent oscillations near shock waves. For unsteady applications, a small displacement hypothesis is used to simulate the motion of the airfoil which allows us to keep a fixed mesh. Steady and unsteady results are presented for a civil aircraft and are compared with experimental values.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.94-101; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991