Gurney襟翼对超临界翼型跨声速气动载荷的影响
Aerodynamic Loads Alteration by Gurney Flap on Supercritical Airfoils at Transonic Speeds
摘要：
采用湍流可压缩KW SST模型，通过求解二维雷诺平均纳维-斯托克斯方程，在跨音速马赫数和攻角范围内，数值研究了Gurney襟翼对超临界NASA翼型的影响。格尼襟翼的高度选择为弦长的1.65%。应用高分辨率网格精确预测翼型附近的流场。在阻力发散马赫数以下，格尼襟翼对气动系数有显著影响，特别是在-1和0 °迎角时，导致L/D比增加50%。在高的马赫数和攻角下，Gurney襟翼失去了它的作用，而清洁翼型具有更好的气动性能，因为它显著地增加了压力和剪切阻力。据观察，格尼襟翼减轻了跨音速λ激波的翼型的两个表面上。此外，它通过改变后缘分离点的位置来改变库塔条件，从而为翼型提供更多的边界环量和升力。
英文摘要：
Effects of a gurney flap were numerically investigated on the supercritical NASA airfoil by solving the two-dimensional Reynolds-averaged Navier-Stokes equations for a range of transonic Mach numbers and angles of attack, using turbulence compressible KW SST model. The height of the gurney flap was selected to be 1.65 percent chord length. A high-resolution mesh was applied to accurately predict the flow field specifically in the vicinity of the airfoil. Below the drag divergence Mach number, the gurney flap has a remarkable influence on the aerodynamic coefficients especially at -1 and 0 degrees angle of attack resulting in 50 percent increase in L over D ratio. At high Mach numbers and angles of attack, Gurney flap loses its effects and the clean airfoil has better aerodynamic performance since it significantly boosts both the pressure and shear drag. It was observed that the gurney flap mitigates the transonic lambda shock on both surfaces of the airfoil. Moreover, it alters the Kutta condition by changing the separation point location at the trailing edge which provides the airfoil more bound circulation and lift force.
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