Abstract Numerical research on the effect of variable droop leading-edge on oscillating NACA 0012 airfoil dynamic stall
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Numerical research on the effect of variable droop leading-edge on oscillating NACA 0012 airfoil dynamic stall

机译：可变下垂前沿对NACA 0012机翼动态失速振荡影响的数值研究

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AbstractDynamic stall occurs when an airfoil is in unsteady motion and the angle of attack is far beyond the static-stall angle. In dynamic stall, lift and pitching moment will fluctuate in a wide range, and the performance of airfoil will get worse. By using the variable droop leading-edge (VDLE), local angle of attack near the leading-edge dynamically decreases when the overall angle of attack gets too large, then the adverse pressure gradient can be reduced. As a result, the formation of leading-edge vortex will be restricted, as well as the flow separation and dynamic stall. In this paper, two VDLE modes are proposed and a series of investigations are performed on the effect of different modes and parameters on dynamic stall control of NACA 0012 airfoil in pitching oscillation. The unsteady Reynolds-averaged Navier–Stokes equations andγ–Reθturbulence model are employed as the governing equations, and the shape modification is realized by the DCP-RBF mesh deformation method. The results suggest that the VDLE modes proposed in this paper can effectively reduce the dynamic stall and significantly improve the aerodynamic characteristics of NACA 0012 airfoil.
机译： 摘要 当机翼处于不稳定状态并且迎角远远超过静态失速角时，就会发生动态失速。在动态失速中，升力和俯仰力矩会在较大范围内波动，并且机翼的性能会变差。通过使用可变下垂前缘（VDLE），当总迎角过大时，靠近前缘的局部迎角会动态减小，从而可以减小不利的压力梯度。结果，将限制前沿涡流的形成以及流动分离和动态失速。本文提出了两种VDLE模式，并研究了不同模式和参数对俯仰振荡中NACA 0012翼型动态失速控制的影响。非稳态雷诺平均Navier–Stokes方程和γ – R e θ 湍流模型用作控制方程，通过DCP-RBF网格变形方法实现形状修改。结果表明，本文提出的VDLE模式可以有效地减少动态失速，并显着改善NACA 0012机翼的空气动力特性。

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