The objective of this effort is to study the aeroelastic characteristics of a flexible membrane wing at different Reynolds numbers using direct numerical simulation and to investigate techniques to reduce the adverse effects of flow separation and unsteady aerodynamics. For the aeroelastic predictions, a first-principles-based approach is undertaken, where the flow solver is fully coupled with the structural dynamics solver. This approach is able to accurately and efficiently predict the unsteady aerodynamics, boundary-layer separation, lift and drag, and the stress and structural deformation of the flexible membrane wing. The focus of this paper is on the systematic validation of this coupled solver for a specific membrane configuration, where extensive experimental measurements are available. Comparisons between the present simulations and experiments are made for the following quantities: 1) mean membrane shape; 2) dominant membrane oscillating frequencies under various conditions; 3) flowfield visualizations; 4) instantaneous velocity field; 5) membrane displacement response to instantaneous flowfield; 6) use of rigid and flexible membranes; 7) distribution of mean velocity field; and 8) distribution of turbulence intensity. Comparisons of these quantities show the favorable agreement of the present prediction against measurement, and hence build a sound validation study for the coupled fluid–structure solver.
Aeroelasticity Validation Study for a Three-Dimensional Membrane Wing
AIAA Journal ; 56 , 6 ; 2361-2371
2018-02-26
11 pages
Article (Journal)
Electronic Resource
English
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