多级环量控制技术增升机理及能效分析

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

多级环量控制技术增升机理及能效分析

杜海¹^,²(), 杨乐杰¹, 李铮³, 徐悦⁴, 孙京阳³, 王宇航⁴

^1.西华大学流体及动力机械教育部重点实验室，成都 610039
^2.西北工业大学翼型叶栅空气动力学国家级重点实验室，西安 710072
^3.中国运载火箭技术研究院空间物理实验室，北京 100076
^4.中国航空研究院，北京 100012

收稿日期:2022-06-30 修回日期:2022-07-28 接受日期:2022-08-08 出版日期:2022-12-25 发布日期:2022-08-18
通讯作者: 杜海 E-mail:duhai@mail.xhu.edu.cn
基金资助:
国家自然科学基金(51806181);翼型、叶栅空气动力学重点实验室基金(614220121030205)

Lifting mechanism and energy efficiency analysis of multistage circulation control technology

Hai DU¹^,²(), Lejie YANG¹, Zheng LI³, Yue XU⁴, Jingyang SUN³, Yuhang WANG⁴

^1.Key Laboratory of Fluid and Power Machinery of Ministry of Education，Xihua University，Chengdu 610039，China
^2.National Key Laboratory of Science and Technology on Aerodynamic Design and Research，Northwest Polytechnical University，Xi’an 710072，China
^3.Laboratory of Science and Technology on Space Physics，China Academy of Launch Vehicle Technology，Beijing 100076，China
^4.Chinese Aeronautical Establishment，Beijing 100012，China

Received:2022-06-30 Revised:2022-07-28 Accepted:2022-08-08 Online:2022-12-25 Published:2022-08-18
Contact: Hai DU E-mail:duhai@mail.xhu.edu.cn
Supported by:
National Natural Science Foundation of China(51806181);National Key Laboratory of Science and Technology on Aerodynamic Design and Research(614220121030205)

摘要/Abstract

摘要：

针对单级环量控制气动效率低、能耗高的不足，设计了一种多级环量增升机翼。通过测力试验，对比研究了多级环量控制在增升方面的控制效果，并且在多级环量控制基础上研究了吹气系数对机翼气动力性能的影响。通过PIV 试验，研究了临界吹气系数前后的流动控制机理。测力结果表明，相比于无环量控制，在输入流量Q=9.84 m³/h时，三喷口吹气（多级环量控制）的最大升阻比提高了95.3%；随着吹气系数的增加，环量控制先后经历分离控制和超环量控制2种阶段，在分离控制阶段，升力系数随吹气系数的增加显著提升，阻力系数先减小后增大；在超环量控制阶段，随吹气系数的增加，升力系数提升效果减弱，阻力系数逐渐增大最后趋于平缓。PIV研究结果表明，在分离控制阶段，随吹气系数的增加，射流分离点沿圆弧后缘下移，增大了速度环量使升力提高，并且尾迹区范围减小、速度提升，使阻力减小；在超环量控制阶段，高速射流使后缘流线产生了大的偏转曲率，起到了气动襟翼的作用，并且在大迎角下兼具控制流动分离的效果。此外，引入了有效升阻比的概念对多级环量增升机翼的气动效率进行评估，发现在分离控制阶段多级环量控制机翼的功率系数较小、有效升阻比最大，气动效率最高。

关键词: 环量控制, 增升, Coanda效应, 风洞试验, PIV

Abstract:

Aiming at the weaknesses of low aerodynamic efficiency and high energy consumption of single-stage circulation control， we design a multistage circulation lift wing. Through the force measurement experiment， the control effect of the multistage circulation control in the aspect of lift increase is comparatively studied， and the influence of the blow coefficient on the aerodynamic performance of the wing is examined based on the multistage circulation control. The flow control mechanism before and after the critical blowing coefficient is studied by a Particle Image Velocimetry （PIV） experiment. The force measurement results show that the maximum lift-to-drag ratio of three slot blowing （multistage circulation control） is improved by 95.3% compared with that of non-circulation control with the input flow Q=9.84 m³/h. With the increase of the blowing coefficient， the circulation control undergoes two stages： separation control and super circulation control. In the separation control stage， the lift coefficient increases significantly with the increase of the blowing coefficient， while the drag coefficient decreases first and then increases. In the super circulation control stage， the increase of the blowing coefficient leads to the weakening of the lifting effect of the lift coefficient， while the drag coefficient gradually increases and finally flattens out. The PIV results show that， in the separation control stage， with the increase of the blowing coefficient， the jet separation point moves down along the back edge of the arc， increasing the velocity circulation to improve the lift， and the wake area decreases and the velocity increases to reduce the drag. In the super circulation control stage， the high-speed jet causes the trailing edge streamlines to produce large deflection curvature， functioning as a pneumatic flap， exhibiting the effect of controlling flow separation at high angles of attack. In addition， the concept of effective lift-to-drag ratio is introduced to evaluate the aerodynamic efficiency of the multistage circulation control wing. It is found that the power coefficient of the multistage circulation control wing is small， the effective lift-to-drag ratio is the largest， and the aerodynamic efficiency the highest in the separation control stage.

Key words: circulation control, lift enhancement, Coanda effect, wind tunnel experiments, Particle Image Velocimetry (PIV)

中图分类号:

V211.4

杜海, 杨乐杰, 李铮, 徐悦, 孙京阳, 王宇航. 多级环量控制技术增升机理及能效分析[J]. 航空学报, 2022, 43(S2): 54-66.

Hai DU, Lejie YANG, Zheng LI, Yue XU, Jingyang SUN, Yuhang WANG. Lifting mechanism and energy efficiency analysis of multistage circulation control technology[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 54-66.

图/表 15

图 1

图2

表1

表2

图3

表3

图4

图5

图6

图7

图8

图9

图10

图11

图12

参考文献 24

1	HARRIS M J. Investigation of the circulation control wing/upper surface blowing high-lift system on a low aspect ratio semispan model[J]. Tort & Insurance Law Journal, 1981:1-85.
2	ZHU H T, HAO W X, LI C, et al. Application of flow control strategy of blowing, synthetic and plasma jet actuators in vertical axis wind turbines[J]. Aerospace Science and Technology, 2019, 88: 468-480.
3	XIAO T H, ZHU Z H, DENG S H, et al. Effects of nozzle geometry and active blowing on lift enhancement for upper surface blowing configuration[J]. Aerospace Science and Technology, 2021, 111: 106536.
4	HARVELL J K, FRANKE M E. Aerodynamic characteristics of a circulation control elliptical airfoil with two blown jets[J]. Journal of Aircraft, 1985, 22(9): 737-742.
5	SOMMERWERK K, KRUKOW I, HAUPT M C, et al. Investigation of aeroelastic effects of a circulation controlled wing[J]. Journal of Aircraft, 2016, 53(6): 1746-1756.
6	LI Y, WANG X N, ZHANG D J. Control strategies for aircraft airframe noise reduction[J]. Chinese Journal of Aeronautics, 2013, 26(2): 249-260.
7	MIKLOSOVIC D, IMBER R, BRITT-CRANE M. Measurements of midspan flow interactions of a low-aspect-ratio circulation control wing[J]. Journal of Aircraft, 2016, 53(6): 1969-1974.
8	WETZEL D A, GRIFFIN J, CATTAFESTA L N III. Experiments on an elliptic circulation control aerofoil[J]. Journal of Fluid Mechanics, 2013, 730: 99-144.
9	JONATHAN K, PANTHE C C, SMIT J E. Applications of circulation control, yesterday and today[J]. International Journal of Engineering, 2010, 4(5):411-428.
10	LOTH J L, FANUCCI J B, ROBERTS S C. Flight performance of a circulation controlled STOL aircraft[J]. Journal of Aircraft, 1976, 13(3): 169-173.
11	ENGLAR R J, HEMMERLY R A, MOORE W H, et al. Design of the circulation control wing STOL demonstrator aircraft[J]. Journal of Aircraft, 1981, 18(1): 51-58.
12	WILDE P, GILL K, MICHIE S, et al. Integrated design of fluidic flight controls for a flapless aircraft[C]∥ 46th AIAA Aerospace Sciences Meeting and Exhibit. Reston: AIAA, 2008.
13	HARLEY C, WILDE P, CROWTHER W. Application of circulation control manoeuvre effectors for three axis control of a tailless flight vehicle[C]∥ 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston: AIAA, 2009.
14	FIELDING J P, MILLS A, SMITH H. Design and manufacture of the DEMON unmanned air vehicle demonstrator vehicle[J]. Proceedings of the Institution of Mechanical Engineers. Part G, Journal of Aerospace Engineering, 2010, 224(4): 365-372.
15	HOHOLIS G, STEIJL R, BADCOCK K. Circulation control as a roll effector for unmanned combat aerial vehicles[J]. Journal of Aircraft, 2016, 53(6): 1875-1889.
16	ENGLAR R J, HUSON G G. Development of advanced circulation control wing high-lift airfoils[J]. Journal of Aircraft, 1984, 21(7): 476-483.
17	ENGLAR R J, SMITH M J, KELLEY S M, et al. Application of circulation control to advanced subsonic transport aircraft, part I - airfoil development[J]. Journal of Aircraft, 1994, 31(5): 1160-1168.
18	ENGLAR R J. Circulation control for high lift and drag generation on STOL aircraft[J]. Journal of Aircraft, 1975, 12(5): 457-463.
19	XU H Y, QIAO C L, YANG H Q, et al. Active circulation control on the blunt trailing edge wind turbine airfoil[J]. AIAA Journal, 2018,56(2):554-70.
20	XU H Y, DONG Q L, QIAO C L, et al. Flow control over the blunt trailing edge of wind turbine airfoils using circulation control[J]. Energies, 2018, 11(3): 619.
21	FU Z, CHU Y, CAI Y, et al. Numerical investigation of circulation control applied to flapless aircraft[J]. Aircraft Engineering and Aerospace Technology, 2020, 92(6): 879-893.
22	CHEN K, SHI Z, ZHU J, et al. Roll aerodynamic characteristics study of an unmanned aerial vehicle based on circulation control technology[J]. Proceedings of the Institution of Mechanical Engineers, 2019, 233(3): 871-882.
23	JONES G S, LIN J C, ALLAN B G, et al. Overview of CFD validation experiments for circulation control applications at NASA[C]∥ 2008 International Powered Lift Conference, 2008.
24	LEFEBVRE A M, ZHA G C. Design of high wing loading compact electric airplane utilizing co-flow jet flow control[C]∥ 53rd AIAA Aerospace Sciences Meeting. Reston: AIAA, 2015.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

参数	设计载荷	精确度/%	准确度/%
X	5/kg	0.18	0.48
Y	2/kg	0.2	0.31
Z	5/kg	0.2	0.5
M_X	1/（kg·m）	0.1	0.27
M_Y	1/（kg·m）	0.085	0.30
M_Z	1/（kg·m）	0.19	0.42

试验条件	喷口	总流量/ （m³·h^-1）	各喷口流量/ （m³·h^-1）
单喷口吹气试验	Slot1	9.84	9.84
	Slot2
	Slot3
双喷口吹气试验	Slot1	9.84	4.92
	Slot2		4.92
	Slot3
三喷口吹气试验	Slot1	9.84	3.28
	Slot2		3.28
	Slot3		3.28

总流量Q/（m³·h ^-¹）	Q_Slot1=Q_Slot2=Q_Slot3	C_μ-_Slot1=C_μ-_Slot2=C_μ-_Slot3
0	0	0
14.76	4.92	0.01
20.85	6.95	0.02
25.56	8.52	0.03
29.52	9.84	0.04
33.01	11.01	0.05
41.73	13.92	0.08
46.68	15.56	0.1

[1]	徐善劼, 吕宏强, 刘中臣, 冷岩, 刘学军. 基于概率模型的声爆试验数据分析[J]. 航空学报, 2023, 44(2): 626269-626269.
[2]	刘中臣, 钱战森, 李雪飞, 冷岩, 郭大鹏. 发动机喷管羽流对近场声爆特性影响的风洞试验技术[J]. 航空学报, 2023, 44(2): 626952-626952.
[3]	黄雄, 曲仕茹, 张恒, 陈显调. 大型客机增升构型缝翼除冰状态失速特性[J]. 航空学报, 2023, 44(1): 627077-627077.
[4]	束珺, 徐东光, 韩志熔, 李斯, 黄雄. 结冰风洞过冷大水滴试验中混合翼设计[J]. 航空学报, 2023, 44(1): 627182-627182.
[5]	罗凯, 王永海, 汪球, 栗继伟, 李峥, 聂春生, 李铮. 高焓风洞中等离子体激励流动控制试验[J]. 航空学报, 2022, 43(S2): 89-96.
[6]	刘传振, 孟旭飞, 刘荣健, 白鹏. 双后掠乘波体高超声速试验与数值分析[J]. 航空学报, 2022, 43(9): 126015-126015.
[7]	齐龙舟, 赵鲲, 冯和英, 张俊龙, 覃晨. 不同冲击距离下斜板开槽对超声速射流冲击噪声的影响[J]. 航空学报, 2022, 43(8): 125712-125712.
[8]	罗佳杰, 宋文滨. 层流机翼及其增升装置嵌套协同优化方法[J]. 航空学报, 2022, 43(8): 125377-125377.
[9]	刘俊, 罗新福, 王显圣. 前缘形状对空腔模型气动特性影响试验[J]. 航空学报, 2022, 43(7): 125235-125235.
[10]	邓志文, 何创新, 刘应征. 耦合粒子图像测速误差的连续伴随数据同化技术[J]. 航空学报, 2022, 43(5): 125305-125305.
[11]	侯英昱, 李齐, 季辰, 刘子强. 超声速低频大抖振气动弹性载荷试验[J]. 航空学报, 2022, 43(3): 626454-626454.
[12]	张桢锴, 贾思嘉, 宋晨, 杨超. 柔性变弯度后缘机翼的风洞试验模型优化设计[J]. 航空学报, 2022, 43(3): 226071-226071.
[13]	曾开春, 寇西平, 杨兴华, 余立, 查俊. 跨声速风洞试验模型主动减振结构优化设计[J]. 航空学报, 2022, 43(2): 224944-224944.
[14]	衣秉立, 刘博宇, 王争取, 张铁军, 鲁丹, 赵彦. 1.2 m高速风洞双天平支撑试验技术[J]. 航空学报, 2022, 43(11): 526794-526794.
[15]	杨钊, 李杰, 牛笑天. 层流机翼飞行验证平台雷诺数效应分析及修正[J]. 航空学报, 2022, 43(11): 527287-527287.

多级环量控制技术增升机理及能效分析

Lifting mechanism and energy efficiency analysis of multistage circulation control technology

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

图/表 15

参考文献 24

相关文章 15

编辑推荐

Metrics

本文评价