Aerodynamic Characteristics of a Deformable Membrane Aerofoil

Abstract:

In the paper, numerical and experimental study of low Reynolds number airflow around the deformable membrane airfoil (DMA) is presented. Simulations of a fluid-structure interaction between the fluid and the DMA were performed. In the experiment, the DMA model was made from a thin PVC sheet, which was wrapped around the steel rod at the leading and trailing edge. Measurements were performed in a wind tunnel at a chord Reynolds number of 85.7·10³, over the angle of attack range from 0° to 15° and DMA shortening ratio from 0.025 to 0.150. Simulations were in an agreement with the experiment, since the average relative difference of coefficient of lift was smaller than 7.3%. For the same value of Reynolds number, DMA shows improved lift coefficient C_y= 2.18, compared to standard rigid airfoils.

• Periodical: Applied Mechanics and Materials (Volume 553)
• Pages: 255-260
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.553.255
• Online since: May 2014
• Authors: Viktor Šajn*, Igor Petrović, Franc Kosel
• Keywords: Deformable Membrane Airfoil, High Lift Aircraft Wing, Interaction Solid-Fluid, Wind Tunnel

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