On the Use of Sweeping Jets to Augment the Lift of a Lambda-Wing
On the Use of Sweeping Jets to Augment the Lift of a Lambda-Wing
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DOI：
10.2514/6.2010-4689
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
Philipp Tewes;L. Taubert;I. Wygnanski
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文献类型：
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作者：
Philipp Tewes;L. Taubert;I. Wygnanski
针对高速亚音速飞行进行优化的超临界机翼需要复杂的辅助高升力系统来起飞和着陆。基于这种翼型，但包含由扫掠喷射执行器增强的简单襟翼的 lambda 翼模型已构建并进行了测试。这些测试的目的是评估这种分离控制方法对实际机翼配置的有效性。在该机翼上进行了力和压力测量，并使用簇绒和瓷土进行了表面流动可视化。改变了这种驱动的强度并评估了其效果。外侧襟翼的执行器方向也发生了改变。第一个襟翼的致动器与自由流对齐，而第二个襟翼的致动器与以 40° 后掠的前缘平行。第二组襟翼的驱动被证明更有效，因为它仅影响减速流分量，并且在展向流上没有浪费动量。这些观察结果再次证实了大展弦比后掠圆柱边界层“独立原理”中的思想。
Super-critical airfoils that are optimized for high speed subsonic flight require complex auxiliary high-lift systems for take-off and landing. A lambda wing model, based on such an airfoil, but containing simple flaps augmented by sweeping jet actuators, was constructed and tested. The purpose of these tests was to assess the efficacy of this method of separation control on a realistic wing configuration. Force and pressure measurements were carried out on this wing as well as surface flow visualization that used tufts and china clay. The strength of this actuation was altered and its effects were assessed. The orientation of the actuators was also altered for the outboard flap. The first flap had actuators aligned with the free stream while the second one had them parallel to the leading-edge that was swept back at 40°. The actuation from the second set of flaps turned out to be more effective because it affected only the decelerating flow component and no momentum was wasted on span-wise flow. These observations reaffirmed the ideas embedded in the boundary layer “independence principle” for large aspect ratio swept back cylinders.