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推导了后掠桨尖剖面法向马赫数和等效迎角与矩形桨尖的关系,指出前飞状态下旋翼后掠桨尖上的法向来流并不一定总比矩形桨叶小的新结论,进一步得出了在后掠桨尖上出现较大法向来流马赫数的解析区间,并给出了克服这种情况出现的解决办法;提出了保持前缘法向来流速度为常数的桨尖设计方案。然后,采用CFD方法,针对后掠新型桨尖旋翼的悬停和前飞跨声速流场进行了数值模拟,并结合理论分析的结果,深入地分析了桨叶后掠对旋翼流场、气动特性的影响,得出了后掠桨尖流场的细节特征,尤其是桨尖附近的激波位置、范围和强度的变化规律。
The relationship between the normal Mach number and the equivalent angle of attack of the swept tip and the tip of the rectangle is deduced. It is pointed out that the normal flow on the swept tip of the rotor in the pre-fly state is not always smaller than that of the rectangular blade , The analytic interval of larger Mach-number in the normal direction appears at the swept-over tip, and the solution to overcome this situation is given. The tip design is proposed to keep the flow velocity in the normal direction of the leading edge constant Program. Then, CFD method is used to simulate the hovering and forward-flight transonic flow fields of a new swept-tip rotor blade. Based on the theoretical analysis, the flow field, aerodynamic characteristics The detail characteristics of the swept-tip flow field are obtained, especially the variation of the shock wave’s location, range and intensity near the tip.