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在西北工业大学NF 3风洞中对OA212MK旋翼翼型加装Gurney襟翼进行了静、动态的测压实验。研究了不同高度的Gurney襟翼在翼型后缘有、无平板(TAB)状态时的增升效果。实验结果表明,高度为0.010c的Gurney襟翼使OA212MK旋翼翼型的最大静态和动态升力系数分别增加了22%和16%,而使OA212MK+TAB的最大静态和动态升力系数分别增加了19%和5%。
Static and dynamic pressure measurement experiments were conducted on the Gurney flaps of the OA212MK rotor airfoil in the Northwest Polytechnic University’s NF 3 wind tunnel. The effect of increasing Gurney flaps with different heights on the trailing edge of the airfoil with and without a flat plate (TAB) was investigated. The experimental results show that the maximum static and dynamic lift coefficients of OA212MK rotor airfoils increase by 22% and 16% respectively with Gurney flaps of 0.010c, and the maximum static and dynamic lift coefficients of OA212MK + TAB are respectively increased by 19% And 5%.