直升机旋翼叶片的空气动力学研究

Mohammad Khairul Habib Pulok, U. Chakravarty
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引用次数: 0

摘要

在任何拥挤的地区,固定翼飞机无法发挥作用,旋翼飞机的垂直起降能力是最合适的选择。旋翼叶片引起的振动是影响直升机性能的一个重要问题。旋翼气动载荷、旋翼动力学和机身动力学是影响直升机振动的主要因素。其中,影响直升机振动的关键因素是气动载荷。气动载荷的确定是旋翼叶片设计和减振的重要依据之一。旋翼谐波载荷是旋翼叶片周围的气流由于旋涡尾迹的快速变化而产生的。叶尖附近循环的快速下降导致叶尖涡,这是叶尖最大升力的原因。因此,叶尖涡成为谐波气动载荷的主要来源。本文以渤105直升机旋翼叶片为研究对象,研究了外气流作用下旋翼叶片的气动特性。计算了不同迎角和方位角下试样的升力和阻力系数。得到了谐振频率和振型。通过小型动叶模型的实验分析,验证了计算结果。研究发现,升力系数随着迎角的增大而增大,直至一个临界值。同样,阻力系数随着迎角的增大而增大。共振频率随动叶的缩放而显著变化。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
A Study of the Aerodynamics of a Helicopter Rotor Blade
In any congested area, where a fixed-wing aircraft cannot perform, rotary-wing counterparts are the best-suited option for its vertical take-off and landing capacity. The vibration induced by the rotor blade is a significant problem in helicopter performances. Rotor aerodynamic loading, rotor dynamics, and fuselage dynamics are the elements that contribute to the vibration of a helicopter. Among these elements, the key reason for the helicopter vibration is the aerodynamic loading. Determining aerodynamic loading is one of the most important criteria to design a rotor blade and to minimize vibration. Rotor harmonic airloads are generated from the rapid variation of flow around the rotor blade due to the vortex wake. A rapid drop in the circulation near the blade tip causes tip vortices which are the reason for the maximum lift at the tip of the blade. Consequently, tip vortices become the primary source of harmonic airloads. In this study, a specimen of Bo 105 helicopter rotor blade is considered to observe the aerodynamic characteristics under the external flow of air. The coefficients of lift and drag of the specimen for different angles of attack and azimuth angles are estimated. The resonance frequencies and the mode shapes are obtained. Computational results are validated by the experimental analyses of a small-scaled model of the rotor blade. From the study, the coefficient of lift is found to increase with the angle of attack up to a critical value. Similarly, the coefficient of drag increases with the angle of attack. The resonance frequencies significantly change with scaling the rotor blade.
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