剪刀尾桨气动干扰与非常规布局参数影响

doi:10.7527/S1000-6893.2025.32181

Abstract

Abstract:

Compared with conventional tail rotors， scissor tail rotors exhibit certain noise reduction advantages due to their modulation effect， but suffer from aerodynamic efficiency loss caused by aerodynamic interference between upper and lower rotors. To improve the aerodynamic efficiency of scissor tail rotors， this paper employs overset grid technology to establish a high-precision numerical simulation method based on Unsteady Reynolds-Averaged Navier-Stokes （URANS） equations. The aerodynamic interference characteristics between the upper and lower scissor tail rotors in hover state is investigated. The research systematically analyzes the influence of configuration parameters including scissor angle， airfoil type， and swept blade tips on aerodynamic performance. Unconventional configurations featuring differential collective pitch settings and varying rotor disk radii between upper and lower rotors are proposed and evaluated.Results indicate that： Under constant total collective pitch， the “U”-type scissor tail rotors total thrust shows positive correlation with scissor angle， while upper and lower rotor thrusts demonstrate a seesaw relationship. Moreover， among three typical helicopter tail rotor airfoils， the OA airfoil achieves optimal hover efficiency. Additionally， swept blade tip configuration delays tip stall without improving maximum hover efficiency. For unconventional configurations： increasing lower rotor radius by 10% enhances maximum hover efficiency by 12.5% compared to conventional designs. Appropriately adjusting lower rotor collective pitch （+2° relative to upper rotor） optimizes load distribution， achieving 2.4% overall efficiency gain.

Key words: scissor tail rotor, aerodynamic characteristics, hover state, aerodynamic interference, unconventional layout

CLC Number:

V211.52

Wangqing ZHU, Chenkai CAO, Guoqing ZHAO, Qinghua ZHU, Haoyu HU. Aerodynamic interference of scissor tail rotor and influence of unconventional layout parameters[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(S1): 732181.

Figures/Tables 25

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References 24

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参数	数值
半径/m	0.409 55
根切	0.2R
弦长/m	0.06
桨叶片数	4
扭转	-11.3，线性
轴间距	0.1R
桨尖速度/（m·s^-1）	208.8
翼型	OA309

网格量/10⁴	拉力系数C_T	扭矩系数C_Q
600	0.019 88	0.002 791
1 400	0.022 25	0.002 653
2 200	0.022 27	0.002 652

参数	数值
半径/m	3.18
根切	0.2R
弦长/m	0.379 6
桨叶片数	4片
扭转	无
轴间距/m	0.609 6
桨尖速度/（m·s^-1）	119.8

构型	上桨盘拉力/N	下桨盘拉力/N	总拉力/N
常规构型	332.28	199.92	532.21
上旋翼后掠	324.65	203.28	527.94
下旋翼后掠	332.88	190.91	523.79
双后掠	325.22	194.19	519.41

下桨盘半径	下桨盘拉力/N	上桨盘拉力/N
R_low=0.8R_up	38.0	352.7
R_low=0.9R_up	85.9	351.5
R_low=1.0R_up	187.8	328.1
R_low=1.1R_up	349.0	303.4

Aerodynamic interference of scissor tail rotor and influence of unconventional layout parameters

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