布孔格尼襟翼对直升机旋翼悬停性能提升的研究

王天健; 韩东; 崔钊

doi:10.13224/j.cnki.jasp.20240268

布孔格尼襟翼对直升机旋翼悬停性能提升的研究

doi: 10.13224/j.cnki.jasp.20240268

王天健^1,,
韩东^1,*, ,,
崔钊²

1.
南京航空航天大学航空学院直升机动力学全国重点实验室，南京 210016
2.
中国飞行试验研究院，西安 710089

基金项目: 主动控制旋翼技术研究项目（FKFB20231108055）；国家自然科学基金（11972181）

详细信息

作者简介:
王天健（1999-），男，硕士生，主要从事旋翼与直升机总体性能研究。E-mail：freljord@nuaa.edu.cn

通讯作者:
韩东（1980-），男，教授，博士，主要从事直升机动力学及其控制、智能旋翼及旋翼飞行器飞行性能等方面的研究。E-mail：donghan@nuaa.edu.cn

中图分类号: V211.52
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出版历程
- 收稿日期: 2024-04-29
- 网络出版日期: 2025-10-23

Perforated Gurney flaps to improve hovering performance of helicopter rotors

WANG Tianjian^1
,,
HAN Dong^{1,*
, ,},
CUI Zhao²

1.
National Key Laboratory of Helicopter Aeromechanics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Chinese Flight Test Establishment，Xi’an 710089，China

摘要

摘要:
对布孔格尼襟翼提升直升机旋翼悬停性能进行了研究，首先采用计算流体动力学（CFD）方法对布孔格尼襟翼的气动特性进行了探讨，建立了加装布孔格尼襟翼的翼型气动模型，在此基础上，将该模型与直升机飞行性能分析模型相耦合，分析了直升机旋翼加装布孔格尼襟翼后的性能提升。结果表明：布孔格尼襟翼上的孔洞射流作用打断了尾缘脱落涡，从而降低了阻力、提升了升阻比。悬停性能分析结果表明：桨叶加装格尼襟翼后，以略微牺牲轻载时性能为代价，能有效提升大载荷时悬停效率并降低需用功率，降低旋翼桨叶迎角，改善桨叶承载分布，且布孔格尼襟翼对性能的提升效果随安装位置向外扩展而增加明显。2%弦长高度、23%孔隙度、加装在桨叶展向80%～95%半径位置的布孔格尼襟翼，在大载荷时可将悬停效率提升10.60%，功率消耗减小10.00%。将旋翼最大拉力提升5.17%，对应悬停效率提升7.82%。
- 格尼襟翼 /
- 直升机 /
- 悬停性能 /
- 布孔格尼襟翼 /
- 需用功率 /
- 悬停效率
Abstract:
A study was conducted for the improvement of hovering performance by perforated gurney flaps’ application on helicopter rotor. First, the aerodynamic characteristics of perforated gurney flaps were discussed using computational fluid dynamics (CFD) method, and then an aerodynamic model of flapped airfoil was established. The performance improvement of the helicopter rotor equipped with perforated gurney flaps was analyzed by the coupling of a helicopter flight performance analysis model with the perforated gurney flap aerodynamic model. The results indicated that the jets brought by the holes interruptted the trailing-edge vortex shedding, thereby reducing the drag and increasing the lift to drag ratio. The analysis of hovering performance showed that after the installation of gurney flaps, at the cost of slightly sacrificing performance under low loads, a significant increment of figure of merit and reduction of power required under high loads was achieved. Also a reduction of angle of attack of rotor blade was convinced, thus the blade load distribution was improved. The afore mentioned effects of perforated gurney flaps increased significantly with the outward expansion of installation position. A 2% chord height, 23% porosity perforated gurney flap equipped at the radial 80% to 95% radius of the rotor blade can increase figure of merit by 10.60% and reduce power required by 10.00% under high loads, thus the maximum thrust of the rotor increased by 5.17% and the corresponding figure of merit increased by 7.82%.
- Gurney flap /
- helicopter /
- hover performance /
- perforated Gurney flap /
- power required /
- figure of merit

HTML

图 1 二维和三维网格及模型

Figure 1. 2D and 3D mesh and model

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图 2 二维^[17]及三维^[11]CFD方法验证

Figure 2. 2D^[17] and 3D^[11] CFD method validation

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图 3 布孔方式对格尼襟翼气动特性影响

Figure 3. Holes’ geometry influence on aerodynamic characteristics of Gurney flap

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图 4 加装格尼襟翼的旋翼桨叶^[6]

Figure 4. Rotor blade equipped with Gurney flap^[6]

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图 5 格尼襟翼几何参数

Figure 5. Gurney flap geometry parameters

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图 6 公式预测布孔格尼襟翼升力系数

Figure 6. Formula prediction of lift coefficient of perforated Gurney flap

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图 7 公式预测布孔格尼襟翼阻力系数

Figure 7. Formula prediction of drag coefficient of perforated Gurney flap

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图 8 直升机悬停性能模型验证

Figure 8. Helicopter hover performance model validation

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图 9 悬停效率曲线

Figure 9. Merit curve in hover

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图 10 孔格尼襟翼于旋翼桨叶上加装方案

Figure 10. Perforated Gurney flap installation sets in rotor blades

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图 11 布孔格尼襟翼对悬停效率影响

Figure 11. Perforated Gurney flaps’ influence on figure of merit

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图 12 布孔格尼襟翼对需用功率影响

Figure 12. Perforated Gurney flaps’ influence on power required

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图 13 布孔格尼襟翼对旋翼最大拉力和悬停效率影响

Figure 13. Perforated Gurney flaps’ influence on the maximum thrust and figure of merit

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图 14 布孔格尼襟翼对旋翼桨盘迎角分布影响

Figure 14. Perforated Gurney flaps’ influence on angle of attack of rotor disc

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表 1 CFD参数设置

Table 1. CFD settings

参数	数值
参数	二维验证	三维验证
翼型弦长/m	1	0.15
格尼襟翼高度与翼型弦长之比/%	0，2，3	6.7
孔隙度/%		0，23
雷诺数/10⁵	21	2.32
第1层网格高度/10⁻⁵m	2.4	2.5

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表 2 布孔格尼襟翼孔洞几何参数设置

Table 2. Perforated Gurney flap geometry sets

编号	示意图	相关参数/mm
编号	示意图	R	a	b
C1 C2		0.8 1.08	1.8 2.5	2.4 3.2
S1		1.62	3.75	2.5
S2		1.62	3.75	5
S3		1.62	3.75	7.5
S4		1.45	3	5
S5		2.16	6.67	5

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表 3 UH-60A直升机主要参数

Table 3. UH-60A helicopter main parameters

	参数	数值及详情
旋翼	半径/m	8.178
	翼型	SC 1095/SC 1094R8
	桨叶片数	4
	转速/（rad/s）	27.0
	弦长/m	0.5273
	挥舞铰偏置/m	0.3817
尾桨	半径/m	1.6764
	翼型	SC 1095
	桨叶片数	4
	转速/（rad/s）	124.62
	弦长/m	0.2469
	负扭/（°）	−18.0

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参考文献(24)

[1]	LIEBECK R H. Design of subsonic airfoils for high lift[J]. Journal of Aircraft, 1978, 15(9): 547-561. doi: 10.2514/3.58406
[2]	NEUHART D, PENDERGRAFT O C. A water tunnel study of Gurney flaps[R]. Hampton, US: Langley Research Center, NASA-TM-4071, 1988.
[3]	JANG C S. Incompressible Navier-Stokes computations of an airfoil with a Gurney flap[D]. San Luis Obispo, US: California Polytechnic State University, 1992.
[4]	JEFFREY D R M. An investigation into the aerodynamics of Gurney flaps [D]. Southampton, US: University of Southampton, 1998.
[5]	KENTFIELD J. The potential of Gurney flaps for improving the aerodynamic performance of helicopter rotors[R]. AIAA-1993-4883, 1993.
[6]	GIBERTINI G, ZANOTTI A, DROANDI G, et al. Experimental investigation of a helicopter rotor with Gurney flaps[J]. The Aeronautical Journal, 2017, 121(1236): 191-212. doi: 10.1017/aer.2016.120
[7]	DEHAEZE F, BAVERSTOCK K D, BARAKOS G N. CFD simulation of flapped rotors[J]. The Aeronautical Journal, 2015, 119(1222): 1561-1583. doi: 10.1017/S0001924000011404
[8]	YEE K, JOO W, LEE D H. Aerodynamic performance analysis of a Gurney flap for rotorcraft application[J]. Journal of Aircraft, 2007, 44(3): 1003-1014. doi: 10.2514/1.26868
[9]	张勇刚, 崔钊, 韩东, 等. 加装格尼襟翼旋翼的直升机飞行性能[J]. 航空学报, 2016, 37(7): 2208-2217. ZHANG Yonggang, CUI Zhao, HAN Dong, et al. Flight performance of helicopter rotors with Gurney flaps[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(7): 2208-2217. (in Chinese ZHANG Yonggang, CUI Zhao, HAN Dong, et al. Flight performance of helicopter rotors with Gurney flaps[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(7): 2208-2217. (in Chinese)
[10]	STACEY S, CONNOLLY N, COURT P. Leonardo helicopter active rotor programmes to improve helicopter comfort & performance[R]. Phoenix, US: 74th American Helicopter Society International Annual Forum and Technology Display, 2018.
[11]	KO L S. An experimental investigation of airfoils with perforated Gurney-type flaps[D]. Montréal, Canada: McGill University, 2011.
[12]	LEE T. Aerodynamic characteristics of airfoil with perforated Gurney-type flaps[J]. Journal of Aircraft, 2009, 46(2): 542-548. doi: 10.2514/1.38474
[13]	PURSER P E, TURNER T R. Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil[R]. Washington, US: Langley Memorial Aeronautical Laboratory, NACA-WR-L-415, 1943.
[14]	MEYER R, HAGE W, BECHERT D W, et al. Drag reduction on Gurney flaps by three-dimensional modifications[J]. Journal of Aircraft, 2006, 43(1): 132-140. doi: 10.2514/1.14294
[15]	TRAUB L W, MILLER A C, REDINIOTIS O. Preliminary parametric study of Gurney flap dependencies[J]. Journal of Aircraft, 2006, 43(4): 1242-1244. doi: 10.2514/1.13852
[16]	KAMNIS S, KONTIS K. Numerical studies on the application of synthetic jets for the active control of subsonic flow configurations[R]. AIAA-2004-2609, 2004.
[17]	LI Yachen, WANG Jinjun, ZHANG Panfeng. Effects of Gurney flaps on a NACA0012 airfoil[J]. Flow, Turbulence and Combustion, 2002, 68(1): 27-39. doi: 10.1023/A:1015679408150
[18]	BACH A B, PECHLIVANOGLOU G, NAYERI C, et al. Wake vortex field of an airfoil equipped with an active finite Gurney flap[R]. AIAA-2015-1271, 2015.
[19]	LIU Tianshu, MONTEFORT J. Thin-airfoil theoretical interpretation for Gurney flap lift enhancement[J]. Journal of Aircraft, 2007, 44(2): 667-671. doi: 10.2514/1.27680
[20]	HAN Dong, DONG Chen, BARAKOS G N. Performance improvement of variable speed rotors by Gurney flaps[J]. Aerospace Science and Technology, 2018, 81: 118-127. doi: 10.1016/j.ast.2018.07.044
[21]	高正, 陈仁良. 直升机飞行动力学[M]. 北京: 科学出版社, 2003: 65-75.
[22]	HILBERT K B. A mathematical model of the UH-60 helicopter[R]. Moffett Field, US: AMSE Research Center, NASA-TM-85890, 1984.
[23]	YEO H, BOUSMAN W G, JOHNSON W. Performance analysis of a utility helicopter with standard and advanced rotors[J]. Journal of the American Helicopter Society, 2004, 49(3): 250-270. doi: 10.4050/JAHS.49.250
[24]	NAGATA J, PIOTROWSKI J L, YOUNG C J. Basline performance verification of the 12th year production UH-60A black hawk helicopter[R]. Washington, US: United States Department of the Army, ADA208671, 1989.