Abstract
Aerodynamic investigation of the deformable membrane airfoil with excess length
Highlights
Deformable airfoils can often be seen in nature: birds, insects, bats, etc
This can be accomplished with the use of rigid structural elements, which provide stiffness, and flexible membrane, which adapts to the shape that provides desired aerodynamic characteristics, for the chosen flight regime
To supplement the bulk knowledge in the field of Micro Aerial Vehicle aero mechanics, the aerodynamic investigation of the deformabilni membranski aeroprofili (DMA) with excess length membrane is performed with the use of the fluid-structure interaction between the DMA and the airflow
Summary
Deformable airfoils can often be seen in nature: birds, insects, bats, etc. Controlled flexibility of the deformable airfoil enables it, to have the best aerodynamic characteristics at current conditions which can be applied in aerial vehicles. Similar procedure was used in [3] and [4], to design the shape of a DMA (sail) with finite difference numerical methods This approach did not take into account viscosity and airflow separation, and was limited to the calculation of airflow around membrane airfoils, with a small profile camber and angle of attack. To properly compute flow separation around DMAs Navier-Stokes equations have to be solved as shown in [7], while to accurately predict the shape of the membrane, the non-linear theory with large displacement must be considered. Because the fluid equations of conservation and the structural equations of state are time dependent, the numerical problem of fluid–structure interaction is solved sequentially, in numerical iteration cycles [9] In this method, the flow field around the membrane airfoil and pressure distribution on a rigid airfoil, is calculated first. All the predefined ranges of the angle of incidence and the excess length ratio are tested, for the non-oscillating DMA configurations
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