Efficient nonlinear static aeroelastic wing analysis |
| |
| Affiliation: | 1. Mechanical Engineering Department, Virginia Polytechnic Institute and State University, c/o Virginia Consortium of Engineering and Sciences, Hampton, VA 23666, USA;2. Multidisciplinary Optimization Branch, NASA Langley Research Center, Hampton, VA 23681, USA;3. Department of Mechanical Engineering, Old Dominion University, Norfolk, VA 23529, USA;1. Israel Aircraft Industries, Tel Aviv, Israel;2. Politecnico di Milano, Department of Aerospace Science and Technology, Milano, Italy;1. Ghent University, Department of Flow, Heat and Combustion Mechanics, Sint-Pietersnieuwstraat 41, B-9000 Ghent, Belgium;2. Ghent University, Department of Industrial Technology and Construction, Valentin Vaerwyckweg 1, B-9000 Ghent, Belgium;3. Ghent University, iMinds Medical IT, IBiTech-bioMMeda, De Pintelaan 185, B-9000 Ghent, Belgium;1. NUS Graduate School for Integrative Science and Engineering, National University of Singapore, Singapore 117456, Singapore;2. Department of Chemical & Biomolecular Engineering, National University of Singapore, Singapore 117585, Singapore |
| |
| Abstract: | The objective of this work is to demonstrate a computationally efficient, high-fidelity, integrated static aeroelastic analysis procedure. The aerodynamic analysis consists of solving the nonlinear Euler equations by using an upwind cell-centered finite-volume scheme on unstructured tetrahedral meshes. The use of unstructured grids enhances the discretization of irregularly shaped domains and the interaction compatibility with the wing structure. The structural analysis utilizes finite elements to model the wing so that accurate structural deflections are obtained and allows the capability for computing detailed stress information for the configuration. Parameters are introduced to control the interaction of the computational fluid dynamics and structural analyses; these control parameters permit extremely efficient static aeroelastic computations. To demonstrate and evaluate this procedure, static aeroelastic analysis results for a flexible wing in low subsonic, high subsonic (subcritical), transonic (supercritical), and supersonic flow conditions are presented. |
| |
| Keywords: | |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
