基于螺旋襟翼的喷流偏转实验研究

汪军; 赖庆仁; 康洪铭; 张刘; 李斌斌; 赵垒; 金熠

doi:10.11729/syltlx20210036

基于螺旋襟翼的喷流偏转实验研究

doi: 10.11729/syltlx20210036

汪军^{1, 2,},
赖庆仁²,
康洪铭²,
张刘^2, ,,
李斌斌³,
赵垒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
计量
- 文章访问数: 530
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- 被引次数: 0
出版历程
- 收稿日期: 2021-04-07
- 修回日期: 2021-05-18
- 网络出版日期: 2021-11-15
- 刊出日期: 2021-11-05

Experimental study on jet turning based on spiral flap

WANG Jun^{1, 2
,},
LAI Qingren²,
KANG Hongming²,
ZHANG Liu^{2
, ,},
LI Binbin³,
ZHAO Lei²,
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.
Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan　621000, China
3.
School of Civil Engineering and Architecture, Southwest University of Science and Technology, 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: 基于阿基米德螺旋线理论，通过逐渐增大曲率半径的方法，设计了一种新型的流动控制襟翼——螺旋襟翼。研究了螺旋襟翼的起始半径、对齐半径等关键控制参数对上表面喷流偏转的影响规律，并与传统基本襟翼的控制效果进行了对比，对二者的控制机理进行了分析。结果表明：所设计的螺旋襟翼最大平均推力偏转角约为19.6°；与基本襟翼相比，螺旋襟翼在大落压比下的平均推力偏转角更大，推力效率更高，这说明改变曲率型面可以促进喷流的流动附着，提高上表面吹气系统性能。
- 螺旋襟翼 /
- 上表面吹气 /
- 喷流偏转
Abstract: A new flow control flap, spiral flap, was designed by gradually increasing the curvature radius based on Archimedes helix theory. The influence of the key control parameters such as the initial radius and alignment radius of the spiral flap on the upper surface jet deflection is studied. The control effect of the spiral flap is compared with that of the traditional basic flap, and the control mechanism of the two is analyzed. The results show that the maximum average thrust deflection angle of the spiral flap is about 20°. Compared with the basic flap, the spiral flap has larger average thrust deflection angle and higher thrust efficiency at large drop pressure ratio, which indicates that changing the curvature profile can promote the flow adhesion of the jet and improve the performance of the upper surface blowing system.
- spiral flap /
- upper surface blowing /
- jet turning

HTML全文

图 1 典型USB系统示意图

Figure 1. Typical USB system diagram

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图 2 上表面喷流装置示意图

Figure 2. Schematic diagram of upper surface jet device

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图 3 螺旋襟翼的曲面设计

Figure 3. Curve design of spiral flap

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图 4 螺旋襟翼安装示意图

Figure 4. Installation schematic diagram of spiral flap

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图 5 基本襟翼示意图

Figure 5. Sketch map of basic flap

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图 6 基本襟翼半径变化时推力偏角和推力效率曲线（δ = 50°）

Figure 6. υ -λ and τ -λ curves basic flap with different radius(δ = 50°)

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图 7 螺旋襟翼对齐半径变化时推力偏角和推力效率曲线（R₀/h = 2.00）

Figure 7. υ -λ and τ -λ curves of spiral flaps with different alignment radius (R₀/h = 2.00)

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图 8 螺旋襟翼对齐半径变化时推力偏角和推力效率曲线（R₀/h = 2.50）

Figure 8. υ-λ and τ-λ curves of spiral flaps with different alignment radius(R₀/h = 2.50)

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图 9 螺旋襟翼对齐半径变化时推力偏角和推力效率曲线（R₀/h = 3.00）

Figure 9. υ -λ and τ -λ curves of spiral flaps with different alignment radius (R₀/h = 3.00)

下载: 全尺寸图片幻灯片

图 10 螺旋襟翼与基本襟翼推力偏角和推力效率曲线对比

Figure 10. υ -λ and τ -λ curves comparison of spiral flap and basic flap

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图 11 喷流偏转控制机理分析示意图

Figure 11. Schematic diagram of jet turning control mechanism analysis

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表 1 TH2003天平载荷与精度

Table 1. Loads and accuracy 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%

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表 2 螺旋襟翼参数表

Table 2. Parameter list of spiral flap

序号	起始半径	对齐半径
1	R₀/h = 2.00	R₁/h = 2.25
2		R₁/h = 2.50
3		R₁/h = 3.00
4		R₁/h = 3.50
5	R₀/h = 2.50	R₁/h = 2.75
6		R₁/h = 3.00
7		R₁/h = 3.50
8		R₁/h = 4.00
9	R₀/h = 3.00	R₁/h = 3.25
10		R₁/h = 3.50
11		R₁/h = 4.00
12		R₁/h = 4.50

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