Experimental research on Aerodynamic Performance of an USPLSC airfoil
Author Affiliations
- 1School of Aeronautics, Northwestern Polytechnical University, Xi`an, China
Res. J. Engineering Sci., Volume 5, Issue (5), Pages 20-30, May,26 (2016)
Abstract
Fre-and-aft symmetrical upper surface protrude lower surface concave (USPLSC) airfoils have been developed for the coaxial rotating wing of an UAV. In order to understand the aerodynamical performance of the airfoil, low speed wind tunnel experiment is carried out to measure lift coefficient, drag coefficient and pressure distribution under wind speed 20~40 m/s. Results are compared with CFD prediction using Fluent software. A satisfied agreement has been achieved and error analysis is provided. The purpose of this study is to conduct a parametric investigation on the performance of USPLSC airfoils for coaxial rotating wing UAV. The main objective of this study is to test USPLSC in wind tunnel and compare the experiment result with CFD simulation result.
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