A modern class of Micro Aerial Vehicles (MAVs) uses Deformable Membrane Wings (DMWs), wing comprising rigid or rigidizable structural elements providing stiffness and flexible membranes providing aerodynamic shape all in a compact and lightweight form. and this work he presents computational and experimental studiesy of of their aerodynamics and static aeroelastic behavior is the investigated topic. To study the characteristics of DMWs, are studied using a parametric physical based two-dimensional Fluid Structure Interaction (FSI) model is built. With the adopting use of thea 2-way coupled FSI algorithm., the The effect of geometrical, material, and flow properties is investigated and the results obtained showed that geometrical and material properties, such as excess length ratio, thickness and Young's modulus, have a significant impact on aeroelastic behavior of DMWs. Validation is carried out using a dedicated experimental setup tested in a low speed wind tunnel facility. Numerical investigations showed to be in a reasonably good agreement with the performed experiments.
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