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首页> 外文会议>BSME International Conference on Thermal Engineering >Design Modification of Airfoil by Integrating Sinusoidal Leading Edge and Dimpled Surface
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Design Modification of Airfoil by Integrating Sinusoidal Leading Edge and Dimpled Surface

机译：通过整合正弦前缘和凹陷表面设计改变翼型

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摘要

Airfoil is widely used for aircraft wings and blades of helicopters, turbines, propellers, fans and compressors. Many researches have been conducted on focusing the leading edge, surface and trailing edge of airfoil in order to maximize airfoil lift and to reduce drag. Literature shows that using protuberances along the leading edge of NACA 2412, it is possible to attain better performance from the baseline. Besides, the inward dimpled surface of NACA 0018 produces lesser drag at a positive angle of attacks. However, there is no literature that integrates sinusoidal leading edge and dimpled to attain the benefits of the both. In this study, simulation has been done for design improvement of airfoil by integrating sinusoidal leading edge and dimpled surface. Simulations have been run using finite element method environment. Significant improvement has been observed from the simulation results.
机译：翼型广泛用于飞机翅膀和直升机，涡轮机，螺旋桨，风扇和压缩机的叶片。在将翼型的前缘，表面和后缘聚焦，以最大化翼型升降并减少阻力，已经进行了许多研究。文献表明，沿着Naca 2412的前缘使用突起，可以从基线获得更好的性能。此外，Naca 0018的内向凹陷表面以正攻角产生较小的拖曳。但是，没有文献，可以集成正弦前缘并凹陷以实现两者的好处。在这项研究中，已经通过整合正弦前缘和凹陷表面来设计模拟来设计改进翼型。使用有限元方法环境进行了仿真。从模拟结果中观察到显着改进。

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