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针对目前前体非对称涡诱导机翼摇滚研究时攻角往往处于静态而没有考虑攻角动态拉起的问题,在北航D4风洞中采用细长旋成体与30°后掠翼的组合体模型,通过不同拉起速度下的机翼摇滚运动实验,分析了攻角拉起速度对前体非对称涡诱导机翼摇滚运动的影响及影响产生的原因;随后通过在快速拉起摇滚运动过程中进行模型表面压力测量,研究了快速拉起机翼摇滚的流动机理.实验结果表明,由于机翼摇滚运动的时间随攻角拉起速度增加而减少,使得在3个不同的拉起速度分区内,摇滚运动呈现为不同的运动形态,其中第3个快速拉起分区内的摇滚运动为与攻角静态时完全不同的类正弦摇滚运动形态.与攻角静态时机翼摇滚的流动机理不同,快速拉起时这种类正弦摇滚运动主要源于前体非对称涡随攻角的演化,前体非对称涡随滚转角的涡型切换不再重要.
In view of the current asymmetric vortex inducing wing rock research angle of attack is often static and did not consider the dynamic angle of attack attack in the Northern Air D4 wind tunnel using slender body and 30 ° swept forward wing combination model Through the experiment of wing rock movement under different pulling speeds, the influence of attack angle on the wing rock induced by asymmetric vortex precursors and the causes of the impact are analyzed. Afterwards, The pressure fluctuation on the model surface was measured and the flow mechanism of the wing-rock was quickly pulled in. The experimental results show that the time of wing-rock movement decreases with the increase of the angle of attack, , The rock movement presents different movement patterns, of which the third rapid pull up the partition rock movement is completely different from the angle of attack static sinusoidal rock-like motion form.With the angle of attack static wing air rock flow mechanism is different from the fast The type of sinusoidal rock motion at pull-up is mainly due to the evolution of the asymmetric vortex with the attack angle of the precursor. The vortex-type switching of the precursor asymmetric vortex with roll angle is no longer important.