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Applying the lifting surface method to the blade tip of a hovering helicopter

机译：将提升面方法应用于悬停直升机的桨叶尖端

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Isser A.; Rosen A.;
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年度 1989
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1. Formulation for flutter and vibration analysis of a hingeless helicopter blade in hover: part Ⅱ. Results of flutter stability and vibration analysis of a hingeless helicopter blade in hover [J] . Ozge Ozdemir Ozgumus, Metin O. Kaya Aircraft Engineering and Aerospace Technology . 2007,第3期

机译：悬停时无铰链直升机叶片颤振和振动分析的公式：第二部分。悬停时无铰链直升机叶片的颤振稳定性和振动分析结果
2. PREDICTION OF THE AERODYNAMIC LOADS ON HELICOPTER BLADES BY LIFTING LINE METHOD [J] . H. DUMITRESCU, V. CARDOS Revue Roumaine de Sciences Techniques . 1995,第2a3期

机译：升降线法预测直升机叶片的气动载荷
3. Improving aeroelastic characteristics of helicopter rotor blades in hovering [J] . Hossam T. Badran, Mohammad Tawfik, Hani M. Negm Advances in Aircraft and Spacecraft Science . 2021,第3期

机译：提高悬伏的直升机转子叶片的空气弹性特性
4. Aerodynamic Low Fidelity Shape Optimization of Helicopter Rotor Blades in Hover Using Genetic Algorithms and The Adjoint Method [C] . Sameh H. Darwish, Mohamed M. Abdelrahman, Ahmed M. Nagib Elmekawy, AIAA aerospace sciences meeting;AIAA SciTech forum . 2018

机译：基于遗传算法和伴随法的悬停直升机旋翼气动低保真形状优化。
5. Helicopter blade tip vortex modifications in hover using piezoelectrically modulated blowing. [D] . Vasilescu, Roxana. 2004

机译：使用压电调制吹气在悬停时调整直升机桨叶尖端涡旋。
6. Estimation and Prediction of Vertical Deformations of Random Surfaces Applying the Total Least Squares Collocation Method [O] . Zbigniew Wiśniewski, Waldemar Kamiński 2020

机译：随机表面垂直变形的估计和预测施加总对方块搭配方法
7. Aerodynamic and acoustic analysis of helicopter main rotor blade tips in hover [O] . Garipova, Lyaysan Ildusovna, Batrakov, Andrei Sergeevich, Kusyumov, Alexander Nikolaevich, 2016

机译：悬停时直升机主旋翼叶尖的气动和声学分析
8. Induced inflow velocity and blade surface pressure measurements for a helicopter model in forward flight. Volume 1: Advance ratio of 0.37, thrust coefficient of 0.0081, and hover tip speed of 710 ft/sec [R] . Elliott, Joe E., Peryea, Martin A., Brand, Albert G., 1992

机译：第1卷：前进比率为0.37，推力系数为0.0081，悬停尖端速度为710英尺/秒。直升机模型在前飞中的感应流入速度和叶片表面压力测量值。

Applying the lifting surface method to the blade tip of a hovering helicopter

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