Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges
Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges
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变形后缘翼型气动性能实验研究
DOI：
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发表时间：
2016
期刊：
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通讯作者：
M. Azarpeyvand
中科院分区：
文献类型：
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作者：
Q. Ai;H. K. Jawahar;M. Azarpeyvand
采用实验和计算相结合的方法，研究了NACA 0012翼型的气动性能和尾迹发展。对NACA 0012翼型进行了变形后缘测试，该翼型具有不同的弧度轮廓，后缘尖端偏转相同。在β=5◦和10◦的后缘偏转角下，对翼型的气动力进行了较大范围的弦基雷诺数和攻角测量。用SpalartAllmaras湍流模型进行了稳态RANS模拟，验证了实验结果。实验结果表明，变形后缘的弯曲型线对翼型的气动性能和进一步提高升力系数的有效性有显著影响。热线测量表明，改变变形后缘弯曲度也会影响下游尾迹的发展。结果表明，与中等弯度的翼型相比，高弯后缘型具有更高的升力系数和更大的最大升力系数，而升阻比略有降低。速度等值线图表明，在大攻角下，翼型后缘高度室化的情况下，后缘附近的分离会进一步延迟。研究表明，在考虑最优气动性能要求的情况下，可以扩展变形尾缘的有效设计空间。研究还表明，为了获得最佳的气动性能，需要对吸力面和压力面进行独立的表面变形，以延迟流动分离的开始。
The aerodynamic performance and wake development of a NACA 0012 airfoil fitted with morphing trailing edges were studied using experimental and computational techniques. The NACA 0012 airfoil was tested with morphing trailing edges having various camber profiles with the same trailing edge tip deflection. The aerodynamic force measurements for the airfoil were carried out for a wide range of chord-based Reynolds number and angles of attack with trailing edge deflection angle of β = 5◦ and 10◦. The experiments were validated with steady-state RANS simulation using SpalartAllmaras turbulence model. Experimental results show that the camber profiles of the morphing trailing edges significantly affect the airfoil’s aerodynamic performance and effectiveness in improving the lift coefficient further by tailoring the morphing profiles. Hot-wire measurements showed that the downstream wake development can also be influenced as a result of changing the morphing trailing edge camber profile. It was found that highly cambered trailing edge profiles provide higher lift coefficients and increased maximum lift coefficient compared to moderately cambered profiles while the lift-to-drag ratio slightly decreases. Velocity contour plots show that the separation near the trailing edge is further delayed at high angles of attack for airfoils with highly chambered morphing trailing edge. This study shows that the effective design space of the morphing trailing edges can be expanded taking into account the optimal aerodynamic performance requirements. The study also suggests that in order to achieve optimum aerodynamic performance, independent surface morphing of the suction and pressure surface camber will be required to delay the onset of flow separation.