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首页> 外文期刊>Journal of aerospace engineering >Experimental Investigation of Asymmetric Vortex Breakdown Flow Control by Microperturbation over Highly Swept Wings
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Experimental Investigation of Asymmetric Vortex Breakdown Flow Control by Microperturbation over Highly Swept Wings

机译：高扫掠翼微扰动控制非对称涡旋的实验研究

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An experimental investigation on asymmetric vortex breakdown flow over three delta wings with sweep angle of 85 degrees, 80 degrees, and 70 degrees was carried out in a wind tunnel at high angles of attack and Reynolds number of 1.215x106 using particle image velocimetry and pressure measurement techniques. First, vortex breakdown flow over delta wings with different sweep angles was measured to confirm the asymmetric flow phenomenon and its formation conditions. Time-averaged vortex breakdown flow over the 70 degrees swept wing was found to be symmetric, whereas flow is asymmetric over the 80 degrees and 85 degrees swept wings. Instability due to crowding together of both leading-edge vortices is the cause of asymmetric vortex breakdown flow. Second, a special test that two nose sections with the same size and shape, named NT1 and NT2, was used to explore the effect of manufacturing imperfection of nose on the asymmetry of vortex breakdown flow was designed. Unpredictable manufacturing imperfection at the nose tip was found to be key natural perturbation of the instability, which led uncertain asymmetric vortex breakdown flow. Finally, the effects of an artificial spherical microperturbation with diameter of 0.2mm fixed at the nose tip were examined to confirm the nondeterminacy of natural perturbations. With artificial microperturbations, rolling moment induced by asymmetric vortex breakdown flow can be controlled in a skillfully deflected manner.
机译：在风洞中以高攻角和雷诺数为1.215x106的风洞进行了三个三角翼掠过角分别为85度，80度和70度的不对称涡流破裂流的实验研究，该过程使用了粒子图像测速和压力测量技术。首先，测量具有不同后掠角的三角翼上的涡旋破坏流，以确认不对称流动现象及其形成条件。发现在70度后掠翼上的时间平均涡流破坏流是对称的，而在80度和85度后掠翼上的流是不对称的。由于两个前沿涡流拥挤而导致的不稳定性是涡流分解流不对称的原因。其次，设计了一个特殊的测试，即使用两个大小和形状相同的鼻部，分别命名为NT1和NT2，以探讨鼻部制造不完善对涡流破裂流的不对称性的影响。人们发现，鼻尖上不可预测的制造缺陷是不稳定性的关键自然扰动，这导致了不确定的不对称涡流破裂流。最后，检查了固定在鼻尖的直径为0.2mm的人工球形微扰的影响，以确认自然扰动的不确定性。借助人工微扰，可以以巧妙的方式控制由不对称涡流破裂流引起的侧倾力矩。

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