Aerodynamic interference characteristics of a new compound configuration helicopter
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摘要:
综合共轴双旋翼直升机高悬停效率和操纵效率的特点及双推力螺旋桨复合式直升机高速前飞性能的优势，将共轴双旋翼应用到双推力螺旋桨复合式直升机上。以X3复合式直升机为基准，将单旋翼改为共轴双旋翼。为研究共轴双旋翼对复合式直升机气动特性的影响，建立全机快速配平方法，并在此基础上针对不同构型直升机开展气动特性分析。结果表明：相较于单旋翼构型，共轴双旋翼构型直升机空气动力学特性具有良好的对称性；在保持较好的高速前飞性能的情况下，共轴双旋翼复合构型可以显著提升悬停和低速飞行性能，悬停效率提升6.8%，100 km/h前飞速度下总需用功率降低23.1%；低速状态下共轴双旋翼对螺旋桨的气动干扰程度明显低于单旋翼构型。
Abstract:By combining the characteristics of high hovering performance and control efficiency of coaxial-rotor helicopters and the advantage of high-speed forward flight performance of double-thrust-propeller compound configuration helicopters, the coaxial rotor was applied to the double-thrust-propeller compound configuration helicopter. The single rotor was changed to a coaxial rotor based on the configuration of the X3 compound helicopter. To study the influence of coaxial rotors on the aerodynamic characteristics of compound configuration helicopters, a fast trim method was established. On this basis, the aerodynamic characteristics of different configuration helicopters were analyzed. The results indicate that the aerodynamic characteristics of the coaxial-rotor helicopter have good symmetry compared with the single-rotor configuration. In the case of maintaining good high-speed forward flight performance, the coaxial-rotor configuration can significantly improve the hovering and low-speed flight performance. When the hovering efficiency is increased by 6.8%, and the forward flight speed is 100 km/h, the total required power is reduced by 23.1%. The aerodynamic interference of the coaxial rotor to the propeller at low speeds is greatly lower than that of the single rotor.
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图 4 机身纵向对称面和螺旋桨平面网格
Figure 4. Grids of longitudinal symmetry plane of fuselage and propeller plane
图 7 机身流场计算结果与试验值对比
Figure 7. Comparison of calculation results of fuselage flow field with test results
图 8 单旋翼构型与共轴双旋翼构型悬停效率对比
Figure 8. Comparison of hovering efficiency between single-rotor configuration and coaxial-rotor configuration
图 10 旋翼拉力和总距随前飞速度的变化
Figure 10. Variation of rotor thrust and collective pitch with forward flight speed
图 11 旋翼桨盘横向剖面压强对比，V=400 km/h
Figure 11. Pressure comparison of transverse profile of rotor disk, V = 400 km/h
图 12 机翼气动特性随前飞速度的变化
Figure 12. Variation of aerodynamic characteristics of wing with forward flight speed
图 13 螺旋桨总距随前飞速度的变化
Figure 13. Variation of propeller collective pitch with forward flight speed
图 14 螺旋桨推进效率随前飞速度的变化
Figure 14. Variation of propeller propulsion efficiency with forward flight speed
图 15 两侧螺旋桨纵向剖面流场分布(V=100 km/h)
Figure 15. Flow field distribution in longitudinal profile of propellers (V = 100 km/h)
图 17 螺旋桨推力与孤立螺旋桨的对比
Figure 17. Comparison of propeller thrust with isolated propeller thrust
半径R/m 转速/(rad·s−1) 桨叶片数 桨叶根切/m 弦长/m 翼型 6.3 36.55 5 1.512 0.385 NACA6412 
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表 2 共轴双旋翼构型
Table 2. Coaxial-rotor configuration
旋翼参数 半径R/m 转速/(rad·s−1) 桨叶片数 上下旋翼间距H/R 旋翼参数 桨叶根切/m 弦长/m 翼型 数值 6.3 36.55 3+3 0.16 数值 1.512 0.321 NACA6412
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