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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (5): 225264-225264.doi: 10.7527/S1000-6893.2021.25264

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

Rotor performance improvement by blade piecewise linear twist

ZHANG Yuhang, HAN Dong, WAN Haoyun   

  1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2021-01-14 Revised:2021-02-21 Published:2021-03-26
  • Supported by:
    National Natural Science Foundation of China(11972181); the Open Research Foundation of the Key Aerodynamics Laboratory(RAL20200104); the Six Talent Peaks Project in Jiangsu Province(GDZB-013); A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institute(PAPD); Postgraduate Research and Practice Innovation Program of Jiangsu Province(KYCX21-0228)

Abstract: To investigate the effect of the blade twist on helicopter rotor performance, a rotor performance calculation model, based on anisotropic composite medium deformation beam model, is derived to predict the power required of a helicopter rotor at any flight speed. The theoretical prediction is consistent with the flight test data, which verifies the effectiveness of the analysis model. According to airfoil distribution of the UH-60 helicopter, the blade is divided into three segments, which are inner, middle and outer segment respectively. And the effect and its mechanism of the three segments on the required power are studied based on the distribution of angle of attack and the lift-drag ratio over the rotor disk. Overall, the faster the helicopter flies forward, the greater the effect of blade twist is. The twist of the inner segment has a negative effect on the rotor performance, but the effect is small. The twist of the middle segment plays a decisive role in improving the airflow environment over the rotor disk, and can reduce the required power by more than 10% in high-speed forward flight. The outer segment is beneficial to power reduction, and the effect is average. A set of piecewise linear twist schemes for each flight velocity are obtained by traversal method, which is better than linear twist scheme in any flight state.

Key words: helicopter, blade twist, rotor performance, performance optimization, power, angle of attack, lift drag ratio

CLC Number: