悬停状态共轴刚性旋翼机身气动干扰特性

doi:10.7527/S1000-6893.2023.29284

Abstract

Abstract:

Experimental and computation studies were conducted on the aerodynamic interaction between coaxial rigid rotor-fuselage in hover. The influence of fuselage aerodynamic interference in hover on the aerodynamic characteristics of coaxial rigid rotor and the pressure distribution on the fuselage surface was analyzed. It is found that the range of high lift areas at the tip of the upper and lower rotor blades is increased， and the power coefficient of the rotors is reduced at the same tension coefficient with the aerodynamic interaction of the fuselage. The rotor maximum Figure of Merit （FM） increases by approximately 4.6%. The fuselage generates vertical down-load， which is about 7% of the rotor pull force， with the influence of rotor downwash flow. Excluding vertical down-load on the fuselage， the maximum FM of the rotor is reduced by about 6% compared to isolated rotors. Under the aerodynamic interaction of rotor， the fuselage generates an upward force moment， which is proportional to the rotor tension coefficient. The surface pressure of the fuselage exhibits an unsteady variation of 4 times the rotational frequency.

Key words: coaxial rigid rotor, aerodynamic interaction, fuselage, wind tunnel test, hover

CLC Number:

V211.52

Pengpeng SUN, Ping’an LIU, Feng FAN, Wei ZENG. Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529284.

Figures/Tables 19

Table 1

Fig.1

Fig.2

Table 2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

References 21

1	吴希明. 共轴刚性旋翼空气动力学问题与研究进展［J］. 南京航空航天大学学报， 2019， 51（2）： 137-146.
	WU X M. Aerodynamic problems and research progresses of rigid coaxial rotor［J］. Journal of Nanjing University of Aeronautics & Astronautics， 2019， 51（2）： 137-146 （in Chinese）.
2	邓景辉. 高速直升机前行桨叶概念旋翼技术［J］. 航空科学技术， 2012， 23（3）： 9-14.
	DENG J H. The ABC rotor technology for high speed helicopter［J］. Aeronautical Science & Technology， 2012， 23（3）： 9-14 （in Chinese）.
3	袁明川，刘平安，樊枫，等. 共轴刚性旋翼气动干扰特性风洞试验研究［J］. 南京航空航天大学学报， 2019， 51（2）： 257-262.
	YUAN M C， LIU P A， FAN F， et al. Wind tunnel test investigation of coaxial rigid rotor aerodynamic interaction［J］. Journal of Nanjing University of Aeronautics & Astronautics， 2019， 51（2）： 257-262 （in Chinese）.
4	ARENTS D N. An assessment of the hover performance of the XH-59A advancing blade concept demonstration helicopter：USAAMRDL-TN-25［R］. Fort Eustis： Army Air Mobility Research And Development Lab， 1977.
5	KIM H W， KENYON A R， DURAISAMY K， et al. Interactional aerodynamics and acoustics of a propeller-augmented compound coaxial helicopter［C］∥ American Helicopter Society Specialists Conference on Aeromechanics. San Francisco： University of Strathclyde， 2008：1-22.
6	KIM H W， KENYON A R， BROWN R E， et al. Interactional aerodynamics and acoustics of a hingeless coaxial helicopter with an auxiliary propeller in forward flight［J］. The Aeronautical Journal， 2009， 113（1140）： 65-78.
7	李文浩. 复合式高速直升机旋翼/机身气动干扰特性的CFD分析［D］. 南京：南京航空航天大学， 2012.
	LI W H. Analysis on aerodynamic interactions of the compound high-speed helicopter rotor/fuselage based on CFD［D］.Nanjing： Nanjing University of Aeronautics and Astronautics， 2012 （in Chinese）.
8	张银. 复合式共轴刚性旋翼直升机气动干扰及飞行特性分析［D］. 南京：南京航空航天大学， 2014.
	ZHANG Y. Research on aerodynamic interaction and flight characteristics of compound helicopter with rigid coaxial rotor［D］.Nanjing： Nanjing University of Aeronautics and Astronautics， 2014 （in Chinese）.
9	胡健平，杨玉成，徐国华，等. 共轴刚性双旋翼直升机悬停旋翼机身干扰流场分析［J］.第33届全国直升机年会论文集.景德镇：中国航空学会直升机分会，2017， 2：29-33.
	Hu J P， YANG Y C， XU G H， et al. Analysis on rotor-fuselage interaction flowfield of helicopter with rigid coaxial rotor impact when hovering［C］∥ The 33th National Helicopter Annual Conference. Jingdezhen： CSAA-Helicopter Branch， 2017， 2：29-33 （in Chinese）.
10	柳家齐，陈荣钱，程佳铭，等. 共轴刚性双旋翼/机身干扰流场数值模拟［J］. 航空动力学报， 2019， 34（11）： 2377-2386.
	LIU J Q， CHEN R Q， CHENG J M， et al. Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction［J］. Journal of Aerospace Power， 2019， 34（11）： 2377-2386 （in Chinese）.
11	PAGLINO V M， BENO E. Full-scale wind tunnel investigation of the advancing blade concept rotor system： USAAMRDL-TR-71-25 ［R］. Fort Eustis： Applied Technology Laboratory， 1971.
12	LORBER P， LAW G， O'NEILL J， et al. Overview of S-97 RAIDER scale model tests［C］∥ The AHS 72 th Annual Forum. West Palm Beach： AHS， 2016：17-19.
13	DENG J H， FAN F， LIU P A， et al. Aerodynamic characteristics of rigid coaxial rotor by wind tunnel test and numerical calculation［J］. Chinese Journal of Aeronautics， 2019， 32（3）： 568-576.
14	邓彦敏，陶然，胡继忠. 共轴式直升机上下旋翼之间气动干扰的风洞实验研究［J］. 航空学报， 2003， 24（1）： 10-14.
	DENG Y M， TAO R， HU J Z. Experimental investigation of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter［J］. Acta Aeronautica et Astronautica Sinica， 2003， 24（1）： 10-14 （in Chinese）.
15	于世美，邓彦敏. 共轴式双旋翼尾迹流场的水洞PIV测量［J］. 北京航空航天大学学报， 2007， 33（6）： 635-639.
	YU S M， DENG Y M. PIV measurements in the wake of coaxial-rotor in water tunnel［J］. Journal of Beijing University of Aeronautics and Astronautics， 2007， 33（6）： 635-639 （in Chinese）.
16	江露生，曹亚雄，刘婷，等. 共轴刚性旋翼悬停状态桨叶表面压力测量试验与计算研究［J］. 北京航空航天大学学报， 2021， 47（12）： 2484-2493.
	JIANG L S， CAO Y X， LIU T， et al. Experimental and computational study on blade surface pressure measurement of coaxial rigid rotor in hovering state［J］. Journal of Beijing University of Aeronautics and Astronautics， 2021， 47（12）： 2484-2493 （in Chinese）.
17	黄明其，王亮权，何龙，等. 共轴刚性旋翼高速直升机风洞试验研究综述［J］. 南京航空航天大学学报， 2021， 53（2）： 216-225.
	HUANG M Q， WANG L Q， HE L， et al. Overview of wind tunnel test for coaxial rigid rotor［J］. Journal of Nanjing University of Aeronautics & Astronautics， 2021， 53（2）： 216-225 （in Chinese）.
18	孙朋朋，刘婷，刘平安，等. 共轴刚性旋翼机身悬停状态气动干扰计算分析［J］. 直升机技术， 2023， 215：8-13.
	SUN P P， LIU T， LIU P A， et al. Numerical analysis of coaxial rigid rotor-fuselage aerodynamic interaction in hover［J］. Helicopter Technique， 2023， 215：8-13 （in Chinese）.
19	LEISHMAN J G. Principles of helicopter aerodynamics［M］. 2nd ed. Cambridge： Cambridge University Press， 2006.
20	MINECK R E， GORTON S A. Steady and periodic pressure measurements on a generic helicopter fuselage model in the presence of a rotor： NASA-TM-2000-210286［R］. Washington， D.C.： NASA， 2000.
21	樊枫. 直升机非定常干扰流场与声场的计算方法研究及应用［D］.南京航空航天大学，2013：25-59.
	FAN F. Research on numerical methods for unsteady interaction flowfield and aerocoustics of helicopters and their applications［D］. Nanjing： Nanjing University of Aeronautics and Astronautics，2013：25-59 （in Chinese）.

名称	要求
机身尺寸/m	长4.16 宽0.71 高0.79
桨毂形式	刚性无铰式
模型旋翼直径	4 m
桨叶片数	上、下旋翼各4片
旋翼旋转方向	上旋翼逆时针、下旋翼顺时针（俯视）
额定转速	907 r/min
上、下旋翼间距	0.14R

状态	总距
上、下旋翼同总距试验	0°，3°，5°，6°，7°，8°，9°，10°，11°，12°
下旋翼扭矩配平试验	上旋翼总距为7°，8°，9°，10°；下旋翼总距根据上旋翼扭矩配平确定

[1]	Kelei WANG, Zhou ZHOU, Minghao LI. Research and experimental validation of loose coupling design method for propulsion wing unit [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(9): 212-229.
[2]	Lixiang WEI, Jinglei XU, Kuangshi CHEN, Shuai HUANG, Jianhui GE, Guangtao SONG. Scheme design and performance study of adjustable vector nozzle for wide-range hypersonic aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631086-631086.
[3]	Yifan YANG, Xiao WANG. Enhanced hybrid vortex particle method for aerodynamic analysis of tiltrotor rotor/wing interactions [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(7): 131040-131040.
[4]	Xian YI, Jinghao REN, Qingren LAI, Yu LIU, Qiang WANG. Icing characteristics of full-scale multi-element configurations of large aircraft: Computation and experiment [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(5): 531575-531575.
[5]	Zhiqiang WAN, Shanshan ZHANG, Xiaozhe WANG, Liang MA, Ao XU, Zhigang WU, Chao YANG. Maneuver load analysis and alleviation technology of flexible aircraft: Review [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 30279-030279.
[6]	Bin LIANG, Junbo ZHAO, Zengliang FU, Jiajian ZHOU, Ping ZHOU, Shiyu ZHANG, Weiqi SUN. Effect of gas mass injection on pitching characteristics of blunt cone [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130822-130822.
[7]	Zhengwu CHEN, Yubiao JIANG, Xiangyu LU, Qiangbin LI. Aerodynamic noise test of open rotor in wind tunnel [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130425-130425.
[8]	Xueliang LI, Chuangchuang LI, Yahan ZHANG, Wei SU, Jie WU. Effect of distributed ablation pattern on hypersonic boundary-layer instability with a flat plate [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130464-130464.
[9]	Ming CAI, Limin GAO, Ruiyu LI, Bo OUYANG, Bo LIU. Establishment of standard model of linear cascade wind tunnel for subsonic compressor [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130547-130547.
[10]	Ruiyu LI, Ming CAI, Bo OUYANG, Limin GAO, Bo LIU, Baojie LIU. Standard cascade test for typical high-load and large turning angle compressor arfoils [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(16): 131651-131651.
[11]	Zhou ZHU, Qi LIN, Cong HE, Lu SHI, Lei ZHAN, Chulun SHEN, Dongbo HAN. Wind tunnel test for coupled motion of spinning projectile based on WDPR suspension support [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(16): 131683-131683.
[12]	Xulong XI, Xiaochuan LIU, Chunyu BAI, Hezhao HAN, Xinyue ZHANG, Xiaocheng LI, Pu XUE, Rangke MU, Xianfeng YANG. Comparison of crash response between fuselage section and full-scale civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(15): 231597-231597.
[13]	Yufeng BAI, Qitong ZOU, Rui HUANG, Haojie LIU, Yuguo RAN. Aeroelastic control of flexible wing with flying-wing configuration and wind tunnel tests [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(14): 331452-331452.
[14]	Chunfeng LIU, Xiaotian HE, Wenbo MIAO, Xuefeng WANG, Xiaoli CHENG. Skin friction measurement technique in rarefied regime and drag force reduction test [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(12): 131028-131028.
[15]	Yifeng ZHANG, Xinguang WANG, Leitao GUO, Yang XU, Qi CHEN. Measurement and analysis of influence of high-speed boundary layer transition on dynamic aerodynamic characteristics of sharp cone [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(12): 131430-131430.

Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 21

Related Articles 15

Recommended Articles

Metrics

Comments