等离子体激励对火星条件下翼型气动特性影响

杨香港; 高永新; 汪忠明; 李益文; 姚程

doi:10.13700/j.bh.1001-5965.2023.0312

等离子体激励对火星条件下翼型气动特性影响

doi: 10.13700/j.bh.1001-5965.2023.0312

1.
合肥工业大学土木与水利工程学院，安徽合肥 230009
2.
空军工程大学等离子体动力学重点实验室，陕西西安 710038

基金项目:

国家自然科学基金(51906054,51776222)

详细信息

通讯作者:
E-mail：yaocheng@hfut.edu.cn

中图分类号: V211.4
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- 被引次数: 0
出版历程
- 收稿日期: 2023-06-05
- 录用日期: 2023-07-21
- 网络出版日期: 2023-08-18
- 整期出版日期: 2025-06-30

Effect of plasma excitation on aerodynamic characteristics of airfoil in Martian atmosphere

1.
College of Civil Engineering，Hefei University of Technology，Hefei 230009，China
2.
Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China

Funds:

National Natural Science Foundation of China (51906054,51776222);

More Information

Corresponding author: E-mail：yaocheng@hfut.edu.cn

摘要

摘要:
由于火星大气密度低、气压小，火星无人机翼型气动性能亟待进一步提高。采用等离子体激励主动流动控制技术提高火星条件下的翼型升力、降低翼型阻力。在火星低雷诺数条件下研究了等离子体激励的作用位置、激励功率及来流攻角对翼型升力和阻力的影响。结果表明：等离子体激励在下表面尾缘区域增升，最大增升率为37%；在下表面前缘区域减阻，最大减阻率为8%；激励功率越大，来流攻角越小，翼型升阻比提升越明显。等离子体激励诱导压力波，在激励的上、下游分别形成增压区和减压区，导致翼型表面形成增压面和减压面。当激励位置靠近尾缘，增压面扩大，翼型上、下表面压差增大，从而实现增升；当激励位置靠近前缘，减压面扩大，翼型压差阻力降低，从而实现减阻。
- 火星无人机 /
- 低雷诺数 /
- 等离子体激励 /
- 增升 /
- 减阻
Abstract:
The aerodynamic characteristics of the airfoil for the Martian unmanned aerial vehicles (UAVs) need to be improved because of the low density and the low pressure in the Martian atmosphere. The active flow control technology with plasma excitation was used to enhance the airfoil lift and reduce the airfoil drag in the Martian atmosphere. Effects of plasma excitation positions, excitation power, and angle of attack on the lift and drag of the airfoil were studied at a low Reynolds number on Mars. It is found that the plasma excitation increases the airfoil lift in the region of the trailing edge of the lower surface with a maximum increase of 37% and reduces the airfoil drag in the region of the leading edge of the lower surface with a maximum drag reduction of 8%. The lift-drag ratio of the airfoil significantly raises when increasing the excitation power and decreasing the angle of attack. The pressure wave induced by the plasma excitation generates a pressurized zone and a depressurized zone in the upstream and downstream regions of the excitation, respectively. Therefore, pressurized and depressurized surfaces appear on the airfoil. When the excitation gets close to the trailing edge, the pressurized surface enlarges, which leads to a higher pressure difference across the upper and lower surfaces of the airfoil and increases the airfoil lift. When the excitation is located near the leading edge, the depressurized surface expands, which reduces the pressure difference of the airfoil and decreases the airfoil drag.
- Martian UAV /
- low Reynolds number /
- plasma excitation /
- lift enhancement /
- drag reduction

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图 1 模型示意图

Figure 1. Schematic diagram of model

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图 2 仿真数据和实验数据的比较

Figure 2. Comparison between simulated data and experiment data

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图 3 不同激励位置的翼型气动特性

Figure 3. Aerodynamic characteristics of airfoil with different excitation positions

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图 4 不同激励功率及攻角的翼型气动特性

Figure 4. Aerodynamic characteristics with different excitation power and angle of attack

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图 5 翼型表面压力分布

Figure 5. Pressure distributions on surface of airfoil

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图 6 翼型流场温度分布

Figure 6. Temperature distribution around airfoil flow field

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图 7 翼型下表面法线方向的速度分布(P₂工况)

Figure 7. Velocity distribution along normal direction on lower surface of airfoil (P₂ case)

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图 8 翼型下表面壁面摩擦系数分布

Figure 8. Skin friction coefficient distribution on lower surface of airfoil

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图 9 压力波发展过程(P₃工况)

Figure 9. Pressure wave propagation for P₃ case

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图 10 启动涡发展过程(P₃工况)

Figure 10. Strat-up vortex development process for P₃ case

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图 11 等离子体激励形成的增压区和减压区(P₃工况，t > 1 s)

Figure 11. Pressurized region and depressurized region induced by plasma excitation (P₃ case, t > 1 s)

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表 1 网格无关性

Table 1. Mesh independence

编号	网格数	C_l	C_d	y⁺
Ⅰ	50 107	0.671 9	0.048 7	≤1
Ⅱ	105 669	0.673 0	0.049 5	≤1
Ⅲ	233 701	0.673 1	0.050 1	≤1

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表 2 不同激励位置下的翼型阻力系数

Table 2. Drag coefficient with excitation positions

激励位置	压差阻力系数	摩擦阻力系数	总阻力系数
无激励	0.037 8	0.016 8	0.054 6
0.1c	0.019 8	0.030 4	0.050 2
0.2c	0.023 5	0.028 9	0.052 4
0.3c	0.027 0	0.027 8	0.054 8
0.4c	0.030 5	0.026 7	0.057 2
0.5c	0.034 1	0.025 4	0.059 5
0.6c	0.037 9	0.024 1	0.062 0
0.7c	0.041 7	0.022 4	0.064 1
0.8c	0.045 4	0.020 4	0.065 8
0.9c	0.048 6	0.017 4	0.066 0

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