R.D. Snyder, J. Hur, D.D. Strong, P.S. Beran

A loosely-coupled procedure for static aeroelastic analysis of high-altitude, long-endurance, joined-wing aircraft is presented. This procedure utilizes a flexible computational framework to integrate fluid dynamics and structural mechanics numerical methods. A variety of computational tools have been and can be integrated within the computational framework; in this paper, a finite-volume Navier-Stokes fluid dynamics solver is coupled with a linear mode-based structural solver. An algebraic spline-based grid deformation method is used to deform the fluid dynamics mesh in response to structural deflections and a conservative and consistent interpolation method is used to transfer loads to the structure. Results are presented for static rigid and static aeroelastic analyses of a joined wing.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 15 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-15; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

aeroelasticity, wings

Bibliothek

2005