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首页> 外文期刊>Journal of the American Helicopter Society >Effect of Sweep on a Pitching Finite Wing
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Effect of Sweep on a Pitching Finite Wing

机译：扫描对俯仰有限翼的影响

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摘要

An investigation was performed into the effect of positive and negative sweep angle on the boundary layer transition and dynamic stall behavior of a finite wing. The finite wing had a 6:1 aspect ratio, modern (SPPS) tip shape, and positive twist, moving the maximum load on the wing away from the wind tunnel wall. Experiments were performed with sweep A = +/- 30 degrees and A = 0 degrees for static polars and sinusoidal pitching. The positively twisted wing shows a S-shaped boundary layer transition on the pressure side similar to that previously seen for helicopter rotor blades in hover. The transition positions on the suction side of the wing are comparable for the same local angle of attack at all values of the sweep A at each of the three pressure sections, and for dynamic pitching motions a hysteresis around the static transition positions is seen. Sweeping the wing led to later stall and higher maximum lift for both static polars and dynamic stall, except for a single case. The negative aerodynamic damping is worse for the swept wing than for the unswept wing, except where the delay of stall led to the flow remaining attached.
机译：研究了正后掠角和负后掠角对有限翼机翼边界层过渡和动态失速行为的影响。有限的机翼具有6：1的纵横比，现代（SPPS）尖端形状和正向扭转力，使机翼上的最大载荷远离风洞壁。对于静态极点和正弦波俯仰，以扫掠A = +/- 30度和A = 0度进行实验。正向扭曲的机翼在压力侧显示出S形边界层过渡，类似于之前在悬停时直升机旋翼桨叶上看到的过渡。机翼吸力侧的过渡位置在三个压力部分的每一个上的扫掠A的所有值下，对于相同的局部迎角都是可比较的，对于动态俯仰运动，可以看到围绕静态过渡位置的磁滞。扫过机翼会导致以后的失速和更高的静态极点和动态失速的最大升力，只有一种情况除外。后掠翼的负空气动力学阻尼比未掠过翼的负空气动力学阻尼更差，除非失速延迟导致气流保持附着状态。

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