多段翼附壁效应环量控制RANS气动特性分析

杜一鸣; 李志浩; 王浩; 黄龙太; 高攀

doi:10.21656/1000-0887.460006

多段翼附壁效应环量控制RANS气动特性分析

doi: 10.21656/1000-0887.460006

杜一鸣^1, ,,
李志浩^1,,
王浩²,
黄龙太³,
高攀³

1.
沈阳航空航天大学航空宇航学院，沈阳 110136
2.
中国航空研究院，北京 100029
3.
中国特种飞行器研究所，湖北荆门 431800

基金项目:

国家自然科学基金青年项目 12202284

详细信息

作者简介:
李志浩(2000—)，男，硕士生(E-mail: lzh_200003013014@163.com)

通讯作者:
杜一鸣(1990—)，男，副教授，博士，硕士生导师(通信作者. E-mail: duyiming@sau.edu.cn)

中图分类号: O354
计量
- 文章访问数: 38
- HTML全文浏览量: 11
- PDF下载量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2025-01-13
- 修回日期: 2025-11-11
- 刊出日期: 2026-05-01

Aerodynamic Characteristic Analysis on Coanda Effects of Multi-Element Airfoils Under Circulation Control Based on RANS

1.
College of Aerospace Engineering, Shenyang Aerospace University, Shenyang 110136, P. R. China
2.
Chinese Aeronautical Establishment, Beijing 100029, P. R. China
3.
China Special Vehicle Research Institute, Jingmen, Hubei 431800, P. R. China

摘要

摘要: 将传统机械式增升装置与先进环量控制技术结合有望改进现有飞行器起降性能. 本文基于Reynolds平均Navier-Stokes(RANS)方法，以二维翼型NLR-7301两段翼为研究对象，分别在主翼和襟翼部位施加环量控制，系统分析了射流喷口位置、高度和动量系数对多段翼气动特性的影响. 研究表明，喷口位置决定了基础气动力水平，喷口靠后会导致Coanda型面过小，附壁效应微弱；而喷口靠前则容易在下表面引起较大分离，降低增升效果. 升力系数基本随射流喷口高度减小和动量系数增大而增大，但存在多参数影响的非线性效应. 喷口高度较小时增升效果较好，过大的喷口射流速度较低，卷吸引射效应减弱，甚至会导致主翼环量控制失效. 计算结果显示，对于NLR-7301两段翼主翼或襟翼环量控制，动量系数0.03是一个较为合适的选择，继续增大会引起控制翼面下表面较大分离，增升效率降低. 从压力分布上看，环量控制能够抬高主翼前缘吸力峰，改善上表面吸力和下表面压力，同时主翼射流的卷吸引射作用有助于消除襟翼后缘边界层分离. 此外，环量控制在三维条件下仍能有效改善机翼气动性能，但其控制效果受展向流动影响，从翼根至翼尖逐渐衰减. 以上结论可为多段翼环量控制设计提供参考，在实际应用中需要通过数值优化寻找控制参数的最优组合，并兼顾升阻特性.
- 环量控制 /
- 附壁效应 /
- 多段翼 /
- RANS /
- 动量系数 /
- 气动特性
Abstract: Combining traditional high lift devices with circulation control is expected to improve the takeoff and landing performance of aircraft. Based on the Reynolds averaged Navier-Stokes (RANS) method, the 2D NLR-7301 2-segment airfoil was taken as the research object. The circulation control was applied to the main element and the flap respectively, and the effects of jet positions, heights, and momentum coefficients on the aerodynamic characteristics of the multi-segment airfoil were systematically investigated. The results show that, the position of the jet determines the basic aerodynamic force. For a too far backward jet position, the Coanda surface will be too small to yield the wall attachment effect. Conversely, for a too far forward jet position, significant separation will easily happen on the lower surface, to reduce the lift-enhancement effect. The lift coefficient generally increases with the decrease of the jet height and the increase of the momentum coefficient, but there is a nonlinear effect by multiple parameters. A smaller jet height can bring a better lift increasement. For high jet heights, the jet velocity is low, to weaken the entrainment effect and potentially cause circulation control failure of the main element. For the circulation control of either the main element or the flap of NLR-7301, 0.03 is an appropriate momentum coefficient, and further increase will cause significant separation of the lower surface, and reduce the efficiency of lift-enhancement. From the perspective of pressure distribution, the circulation control can elevate the suction peak at the leading edge of the main element, and improve the upper surface suction and lower surface pressure. At the same time, the entrainment effect of the main element jet flow helps to eliminate the boundary layer separation at the trailing edge of the flap. Furthermore, the circulation control can still effectively enhance the aerodynamic performance of the wing under 3D conditions. However, its control effect is affected by the spanwise flow and gradually diminishes from the wing root to the tip. The above conclusions provide a reference for the design of the circulation control of multi-element airfoils. In practical applications, numerical optimization is required to find the optimal combination of control parameters, in view of both lift and drag characteristics.
- circulation control /
- wall attachment effect /
- multi-element airfoil /
- RANS /
- momentum coefficient /
- aerodynamic characteristics

HTML全文

图 1 S809翼型环量控制外形对比及计算网格

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 1. The geometry comparison and computational grids of S809 and S809-CC

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图 2 S809和S809-CC翼型表面压力分布与参考结果^[36]的对比

Figure 2. Surface pressure distribution comparisons of S809 and S809-CC with ref. [36]

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图 3 S809翼型环量控制前后流动特性对比

Figure 3. Comparisons of flow characteristics before and after circulation control of the S809 airfoil

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图 4 NLR-7301多段翼及其计算网格

Figure 4. The geometry and computational grid of the NLR-7301 multi-element airfoil

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图 5 NLR-7301多段翼构型压力分布

Figure 5. The pressure distributions of NLR-7301 multi-elementairfoil

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图 6 NLR-7301环量控制构型及计算网格

Figure 6. The schematic diagram and grid of NLR-7301 with circulation control

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图 7 力系数收敛曲线

Figure 7. The convergence history of force coefficients

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图 8 NLR-7301-CC_flap气动特性变化曲线

Figure 8. The aerodynamic characteristic variation curves of NLR-7301-CC_flap

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图 9 NLR-7301-CC_flap翼型不同开口位置下的流场图

Figure 9. The flow fields of NLR-7301-CC_flap in different positions of the jet

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图 10 不同动量系数下NLR-7301-CC_flap翼型流场图

Figure 10. The flow fields of NLR-7301-CC_flap under different momentum coefficients

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图 11 NLR-7301-CC_flap翼型流场图(c_j=0.7c_flap，h=0.000 15c)

Figure 11. The flow field of NLR-7301-CC_flap (c_j=0.7c_flap, h=0.000 15c)

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图 12 NLR-7301-CC_flap环量控制前后压力分布

Figure 12. The pressure distributions before and after circulation control of NLR-7301-CC_flap

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图 13 NLR-7301-CC_main翼型气动特性变化曲线(c_j=0.9c_main)

Figure 13. The aerodynamic characteristic variations of NLR-7301-CC_main (c_j=0.9c_main)

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图 14 不同动量系数的流场图(h=0.001c)

Figure 14. The flow fields with different momentum coefficients (h=0.001c)

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图 15 不同喷口高度对应流场图(C_μ=0.03)

Figure 15. The flow fields with different jet heights (C_μ=0.03)

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图 16 NLR-7301-CC_main环量控制前后压力分布图

Figure 16. The pressure distributions before and after circulation control of NLR-7301-CC_main

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图 17 机翼模型及计算网格

Figure 17. The wing model and computational mesh

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图 18 3D机翼气动特性变化曲线

Figure 18. The aerodynamic characteristic variations of the 3D wing

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图 19 3D机翼气动特性变化曲线

Figure 19. The aerodynamic characteristic variations of the 3D wing

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图 20 机翼不同站位流场图(y/b=0.1，0.5，0.9)

Figure 20. The flow fields of different wing positions (y/b=0.1, 0.5, 0.9)

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表 1 NLR-7301多段翼构型的气动力系数

Table 1. Aerodynamic coefficients of the NLR-7301 multi-element airfoil

α/(°)	turbulence model	C_L	C_D
6.0	k-ω SST	2.399	0.030 5
	γ-Re_θt	2.455	0.026 5
	ref. [44]	2.499	0.027 4
	exp	2.416	0.022 9
13.1	k-ω SST	3.020	0.066 5
	γ-Re_θt	3.168	0.055 8
	ref. [44]	3.272	0.051 2
	exp	3.141	0.044 5

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