NACA0012翼型气动性能试验研究

2022 International Conference on Intelligent Controller and Computing for Smart Power (ICICCSP) Pub Date : 2022-07-21 DOI:10.1109/ICICCSP53532.2022.9862440

A. Yadav, Dhruv P. Suthar, Hetal Bhatiya, Aniruddh Marakana, Mohammad Shadab Ghanchi, Sathish Dharmalingam

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引用次数: 0

摘要

在低速亚音速风洞中测量了不同雷诺数下不同迎角的气动特性，以扩展对NACA 0012翼型压力分布的了解。在攻角从−30°到+30°，速度从10m /s到25m /s的范围内进行了实验。升力系数和阻力系数为NACA 0012翼型是通过测量压力分布从位于翼型表面的压力端口获得。

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Experimental Investigations on Aerodynamic Performances of NACA0012 Airfoil

The aerodynamic characteristics for the various angles of attack at different Reynolds numbers with a view to extending the knowledge of the pressure distribution over the NACA 0012 airfoil have been measured in a low-speed subsonic wind tunnel. Experiments were carried out by varying the angle of attack from −30 to +30 degrees and the velocity varied from 10 m/s to 25 m/s. The lift coefficient and drag coefficient for the NACA 0012 airfoil are obtained by measuring the pressure distribution from the pressure ports situated over the airfoil surface.

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2022 International Conference on Intelligent Controller and Computing for Smart Power (ICICCSP)

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