Hover performance of helicopter main and tail rotors with swirl velocities
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National Natural Science Foundation of China (11972181); the Six Talent Peaks Project in Jiangsu Province (GDZB-013); the Open Research Foundation of the Key Rotor Aerodynamics Laboratory (2005RAL20200104)


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    It is important to quickly predict the hover performance of main and tail rotors with sufficient precision for helicopter design. To investigate the effects of swirl velocities on the hover performance of main and tail rotors, and give a better prediction for the hover performance, a flight performance model was derived and a swirl velocity model was coupled into it. The test data of the UH-60A helicopter were used for validation. When the blade loading coefficient of the main rotor was higher than 005, the effects of the swirl velocities on the main rotor power became significant. The swirl velocities increased the profile torque of the main rotor. The increased torque required the tail rotor to produce more thrust with more power consumption. At a higher blade loading coefficient of the main rotor of 012, the swirl velocities increased the main rotor power, tail rotor power and total power by 380%, 524% and 508%, respectively. The profile power increase of the main rotor caused by the profile swirl velocity was less than that of the induced swirl velocity, but the power increase was higher at high rotor blade loadings. Considering the swirl velocities in the main rotor can improve the prediction precision of the hover performance, especially at high blade loadings

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YANG Kelong, HAN Dong. Hover performance of helicopter main and tail rotors with swirl velocities[J].航空动力学报,2021,36(1):119~129. YANG Kelong, HAN Dong.[J]. Journal Of Aerospace Power,2021,36(1):119-129.

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  • 收稿日期:2020-06-14
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  • 在线发布日期: 2021-02-04
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