Analysis of aerodynamic characteristics of helicopter biplane tailplane

直升机双层平尾构型气动特性分析

National Key Laboratory of Helicopter Aeromechanics, China Helicopter Research and Development Institute, Jingdezhen 333000, China

Received: 9 April 2023

Abstract

To analyze the aerodynamic characteristics of helicopter biplane tailplane, computational models for helicopter biplane tailplane and monoplane tailplane were established via CFD. The aerodynamic characteristics of different configurations of tailplanes at low speed forward flight and high angle of attack was obtained. The aerodynamic characteristics and flow characteristics of biplane/monoplane tailplane were analyzed. The mechanism of biplane tailplane to improve the longitudinal static stability at low speed forward flight and high angle of attack was investigated. The results show that the biplane tailplane can improve the helicopter pitch moment surge at low speed forward flight by restraining the rotor/tailplane interference, comparing with the monplane tailplane, the pitch moment of the biplane tailplane was reduced by about 56.8% at an advance ratio of 0.05. The stall angle of attack and maximum pitch moment of the biplane tailplane were larger, which can enhance the helicopter longitudinal static stability at high angle of attack, comparing with the monplane tailplane, the pitch moment of the biplane tailplane increased by about 60.1% at an attack angle of 20°.

摘要

为分析双层平尾气动特性, 采用CFD方法建立了直升机平尾计算模型, 获得了低速前飞和机身大迎角状态不同构型平尾的气动特性, 分析了单层和双层平尾构型的气动特性和流场特点, 研究了双层平尾对低速前飞状态和大迎角状态的纵向静稳定性改善作用机理。结果表明: 双层平尾构型通过抑制旋翼/平尾干扰改善低速前飞状态下的直升机俯仰力矩突增问题, 前进比为0.05时, 双层平尾俯仰力矩比单层平尾减小56.8%;双层平尾的失速迎角和最大俯仰力矩增大, 从而增强直升机大迎角状态的纵向静稳定性, 迎角20°时, 双层平尾俯仰力矩比单层平尾增大60.1%。

1. LEISHMAN J G. Principles of helicopter aerodynamics[M]. 2nd ed. Cambridge: Cambridge University Press, 2006 [Google Scholar]
2. NI Xianping. Analysis of some aerodynamic design problems for a helicopter[J]. Helicopter Technique, 1995(2): 1–11 [Article] (in Chinese) [Google Scholar]
3. ZHANG Chenglin, GUO Caigen. Overall design of helicopter[M]. Beijing: National Defense Industry Press, 2006 (in Chinese) [Google Scholar]
4. WANG Jian, GUO Gaofeng, YAN Xiaochao, et al. Design and analysis of a vortex generator on horizontal tail[J]. Advances in Aeronautical Science and Engineering, 2022, 13(6): 116–124 [Article] (in Chinese) [NASA ADS] [Google Scholar]
5. WANG Xinlei, LI Shengwei, LIN Changliang. Aerodynamic characteristics of helicopter with leading-edge slatted horizontal tail[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2020, 52(2): 288–293 [Article] (in Chinese) [Google Scholar]
6. MOEDERSHEIM E, LEISHMAN J G. Investigation of aerodynamic interactions between a rotor and a t-tail empennage[J]. Journal of the American Helicopter Society, 1998, 43: 37–46 [Article] [CrossRef] [Google Scholar]
7. GREGORIO F D. Flow field characterization and interactional aerodynamics analysis of a complete helicopter[J]. Aerospace Science & Technology, 2012, 19(1): 19–36 [CrossRef] [Google Scholar]
8. SUN Zhengrong, YANG Yongdong. Effects of rotor on fuselage and horizontal tail aerodynamics in hover and low speed forward flight[J]. Acta Aerodynamica Sinica, 1999, 17(3): 243–250 [Article] (in Chinese) [Google Scholar]
9. BIAVA M, VIGEVANO L. Simulation of a complete helicopter: A CFD approach to the study of interference effects[J]. Aerospace Science and Technology, 2012, 19(1): 37–49 [Article] [CrossRef] [Google Scholar]
10. RINKER M, RIES T, EMBACHER M, et al. Simulation of rotor-empennage interactional aerodynamics in comparison to experimental data[C]//75th Annual Forum of the Vertical Flight Society, 2019 [Google Scholar]
11. TAN Jianfeng, WANG Haowen, WU Chao, et al. Rotor/empennageunsteady aerodynamic interaction with unsteady panel/viscous vortex particle hybrid method[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(3): 643–656 [Article] (in Chinese) [Google Scholar]
12. FAURE T M, DUMAS L, MONTAGNIER O. Numerical study of two-airfoil arrangements by a discrete Vortex method[J]. Theoretical & Computational Fluid Dynamics, 2020, 34(1/2): 79–103 [CrossRef] [Google Scholar]
13. MOSCHETTA J M, THIPYOPAS C. Aerodynamic performance of a biplane micro air vehicle[J]. Journal of Aircraft, 2007, 44(1): 291–299 [Article] [CrossRef] [Google Scholar]
14. JONES R, CLEAVER D J, GURSUL I. Aerodynamics of biplane and tandem wings at low Reynolds numbers[J]. Experiments in Fluids, 2015, 56(6): 1–25 [CrossRef] [Google Scholar]
15. CHEN Yongliang. Experimental study on the distributed electric propulsion aircraft[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019 (in Chinese) [Google Scholar]
16. ZHANG Qing, YE Zhengyin. Computational investigations for aerodynamic characteristic analysis of low reynolds number doubly-tandem wing configurations[J]. Engineering Mechanics, 2019, 36(10): 244–256 [Article] (in Chinese) [Google Scholar]
17. KELAIDIS M, ALLONGUE M, LEYDER S. The biplane stabilizer of the H160 helicopter-design & development[C]//The ERF 42nd Annual Forum, 2016 [Google Scholar]
18. SUN Huixun, SUN Pengpeng, LIN Yongfeng, et al. Analysis on the suppression mechanism of biplane tailplane to rotor/empennage aerodynamic interaction[J]. Helicopter Technique, 2021, 210(4): 1–6 [Article] (in Chinese) [Google Scholar]
19. BLACHA M, FINKA, EGLINP, et al. “CLEANSKY2”: exploring new rotorcraft high speed configurations[C]//The 43rd European Rotorcraft Forum, 2017 [Google Scholar]
20. VELDHUIS L. Aerodynamic installation effects of lateral rotors on a novel compound helicopter configuration[C]//The AHS International 74th Annual Forum & Technology Display, 2018 [Google Scholar]
21. HE Xiaoping, HAN Dong, YANG Kelong, et al. Flight performance of compound helicopter with twin propeller[J]. Journal of Aerospace Power, 2020, 35(4): 815–822 [Article] (in Chinese) [Google Scholar]
22. RAYMOND E M, GORTON S A. Steady and periodic pressure measurements on a generic helicopter fuselage model in the presence of a rotor[R]. NASA TM 2000-210286, 2000 [Google Scholar]
23. YUAN Guangtian, HUANG Peng, HAN Yixin. Mechanism of flow separation induced by aircraft wing-body interference[J]. Chinese Journal of Applied Mechanics, 2020, 37(1): 98–104 [Article] (in Chinese) [Google Scholar]
24. XU Min, AN Xiaomin. Analysis and computing method of aircraft aerodynamics[M]. Xi'an: Northwestern Polytechnical University Press, 2012: 116–117 (in Chinese) [Google Scholar]