机翼上表面喷流偏转被动控制实验研究

汪军; 张刘; 李斌斌; 赵垒; 李昌; 金熠

doi:10.11729/syltlx20210027

机翼上表面喷流偏转被动控制实验研究

doi: 10.11729/syltlx20210027

汪军^{1, 2,},
张刘^2, ,,
李斌斌³,
赵垒²,
李昌²,
金熠^4, ,

1.
中国科学技术大学工程科学学院精密机械与精密仪器系，合肥　230031
2.
中国空气动力研究与发展中心低速空气动力研究所，四川绵阳　621000
3.
西南科技大学土木工程与建筑学院，四川绵阳　621000
4.
中国科学技术大学工程与材料科学实验中心，合肥　230031

基金项目: 中国空气动力研究与发展中心基础和前沿技术研究基金（FFTRF20171001）

详细信息

作者简介:
汪军：（1991–），男，安徽巢湖人，硕士研究生，助理工程师。研究方向：动力增升技术。通信地址：四川省绵阳市涪城区二环路南段6号（621000）。E-mail：wang07@mail.ustc.edu.cn

通讯作者:
E-mail：lzh2607@126.com；

yjin@ustc.edu.cn

中图分类号: V211.73
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- 文章访问数: 359
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- PDF下载量: 24
- 被引次数: 0
出版历程
- 收稿日期: 2021-03-18
- 修回日期: 2021-05-20
- 网络出版日期: 2021-12-10
- 刊出日期: 2021-12-30

Experimental study of passive control of jet deflection on wing upper surface

WANG Jun^{1, 2
,},
ZHANG Liu^{2
, ,},
LI Binbin³,
ZHAO Lei²,
LI Chang²,
JIN Yi^{4
, ,}

1.
Department of Precision Machinery and Precision Instruments, School of Engineering Science, University of Science and Technology of China, Hefei　230031, China
2.
School of Civil Engineering and Architecture, Southwest University of Science and Technology; Mianyang Sichuan　621000, China
3.
Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan　621000, China
4.
Engineering and Materials Science Experimental Center, University of Science and Technology of China, Hefei　230031, China

摘要

摘要: 通过静态推力实验，研究了襟翼形状对机翼上表面喷流偏转的影响。在此基础上，通过涡流发生器对喷流偏转进行被动控制，研究了涡流发生器安装位置、安装角和涡流发生器高度对喷流偏转性能的影响。结果表明：喷流偏角在襟翼偏角为30°时达到最大值，并随襟翼半径增大而增大；使用涡流发生器有助于促进喷流附着、增大喷流偏角；安装角和涡流发生器高度是影响喷流偏转性能的关键参数。
- 喷流 /
- 上表面吹气 /
- 涡流发生器 /
- 控制实验
Abstract: The effect of flap shape on jet deflection on the upper surface of the wing is studied by the static thrust experiment. On this basis, the jet deflection is passively controlled by the vortex generator, and the effects of the installation position, installation angle and height of the vortex generator on the jet deflection performance are studied. The results show that the jet deflection angle reaches the maximum when the flap deflection angle is 30° and increases with the increase of the flap radius. The use of vortex generators helps to promote the jet adhesion and to increase the jet deflection angle. Its height and installation angle are the key parameters that affect the deflection performance of the jet.
- jet /
- upper surface blowing /
- vortex generator /
- control experiment

HTML全文

图 1 典型USB系统示意图

Figure 1. Sketch of typical USB system

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图 2 上表面喷流实验装置

Figure 2. Design drawing of jet simulation device

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图 3 喷流模拟装置设计图

Figure 3. Design drawing of jet simulation device

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图 4 襟翼设计图

Figure 4. Design drawing of flap

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图 5 涡流发生器

Figure 5. Vortex generator

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图 6 测量段总压耙布置示意图

Figure 6. Layout diagram of total pressure rake in measuring section

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图 7 重复性实验状态照片

Figure 7. Photo of repeatability test status

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图 8 巡航状态F₁-λ 曲线

Figure 8. Thrust resultant force-drop ratio curves of cruise status

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图 9 襟翼角度变化υ-λ曲线（R/h = 1.5）

Figure 9. υ-λ curve of flap with different angles (R/h = 1.5)

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图 10 襟翼曲率半径变化υ-λ曲线

Figure 10. υ-λ curve of flap with different radius of curvature

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图 11 涡流发生器安装情况

Figure 11. VG installation

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图 12 VG安装位置变化υ-λ曲线

Figure 12. υ-λ curve of VG with different locations

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图 13 VG安装角度变化时的υ-λ曲线

Figure 13. υ-λ curve of VG with different installation angles

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图 14 VG高度变化时的υ-λ曲线

Figure 14. υ-λ curve of VG with different heights

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图 15 VG控制影响υ-λ曲线

Figure 15. υ-λ curve of VG influence

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图 16 VG控制影响τ-λ曲线

Figure 16. τ-λ curve of VG influence

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表 1 TH2003天平载荷及精度表

Table 1. Load and precision of TH2003 balance

分量 F_x F_y F_z M_x M_y M_z

设计载荷 1000 N 1500 N 1000 N 300 N·m 500 N·m 600 N·m
精度 0.02% 0.01% 0.01% 0.02% 0.02% 0.01%

下载: 导出CSV

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