局部振动对火星环境下薄翼型气动性能的影响

陈肇麟; 陆政旭; 肖天航; 邓双厚

doi:10.13700/j.bh.1001-5965.2022.0032

局部振动对火星环境下薄翼型气动性能的影响

doi: 10.13700/j.bh.1001-5965.2022.0032

南京航空航天大学航空学院飞行器先进设计技术国防重点学科实验室，南京 210016

基金项目: 国家自然科学基金(11672133,12002161)；江苏高校优势学科建设工程

详细信息

通讯作者:
E-mail： xthang@nuaa.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2022-01-19
- 录用日期: 2022-03-11
- 网络出版日期: 2022-03-18
- 整期出版日期: 2023-11-30

Effect of local oscillation on aerodynamics of thin airfoil in Mars environment

National Defense Key Laboratory of Aircraft Advanced Design Technology，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Funds: National Natural Science Foundation of China (11672133,12002161)；Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: E-mail：xthang@nuaa.edu.cn

摘要

摘要:
火星的稀薄大气环境迫使无人机在亚临界雷诺数范围工作，低雷诺数层流分离问题给无人机气动性能带来极其不利的影响。同时，火星大气的声速较低，使无人机运行的马赫数更高，压缩效应增强并可能产生激波。为研究火星环境下翼型局部振动的流动控制作用，采用基于动网格的数值方法对非定常流场进行模拟。选取NACA5605低雷诺数薄翼型，雷诺数为1.5×10⁴，马赫数为0.43和0.63。时均流场和时均气动力系数结果显示：翼型局部振动能够明显减少时均分离区的大小，起到增升减阻的作用。非定常流场表明流动控制机理在于振动产生的涡流运动抑制了翼型尾缘附近的层流分离。研究了不同振幅、频率和振动位置下的流动控制效果。最佳参数下，马赫数为0.43时升阻比最多提高24.7%，马赫数为0.63时升阻比最多提高52%。
- 火星环境 /
- 低雷诺数 /
- 层流分离 /
- 局部振动 /
- 流动控制
Abstract:
The thin atmosphere of Mars constrains the MAV in the subcritical Reynolds number regime, where the laminar boundary layer separation extremely adversely affects the aerodynamic performance of UAVs. Meanwhile, the low sound velocity of the Martian atmosphere results in a higher Mach number of UAVs, which enhances the compression effect and may generate shock waves. The numerical approach based on the dynamic mesh is used to model the unsteady flow field and examine the flow control effect of the airfoil local oscillation with the atmospheric characteristics of Mars. The NACA5605 thin airfoil is selected, the Reynolds number is 1.5×10⁴, and the Mach number is 0.43 and 0.63. The airfoil local oscillation can greatly reduce the size of the separation zone, increasing lift and decreasing drag, according to the results of the time-averaged flow field and time-averaged aerodynamic coefficient. The unsteady flow field shows that the flow control mechanism is that the vortex motion generated by oscillation restrains the laminar flow separation near the trailing edge of the airfoil. The flow control efficiency under different amplitudes, frequencies, and oscillation locations is studied. Under the optimal parameters, the lift-to-drag ratio is improved up to 24.7% at 0.43 Mach number while 52% at 0.63 Mach number.
- Mars environment /
- low Reynolds number airfoil /
- laminar separation /
- local oscillation /
- flow control

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图 1 局部振动变形草图

Figure 1. Sketch of deformation of local oscillation

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图 2 网格和边界条件

Figure 2. Mesh and boundary condition

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图 3 不同网格的非定常升力系数

Figure 3. Unsteady lift coefficients of different meshes

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图 4 不同时间步长的非定常升力系数

Figure 4. Unsteady lift coefficients of different time steps

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图 5 三角形翼型

Figure 5. Triangular airfoil

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图 6 三角形翼型计算值和实验值的对比

Figure 6. Comparison between calculated results and experimental results of triangular airfoil

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图 7 NACA5605翼型时均流场

Figure 7. Time-average flow fields of NACA5605 airfoil

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图 8 工况1和工况2时均压力系数分布对比

Figure 8. Comparison of time-average pressure coefficient distribution between Case1 and Case 2

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图 9 工况1和工况2的非定常流场

Figure 9. Unsteady flow field of Case 1 and Case 2

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图 10 不同振幅下气动力的相对变化比例

Figure 10. Relative change ratio of aerodynamic force at different amplitudes

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图 11 不同振幅下的时均流场

Figure 11. Time-average flow field at different amplitudes

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图 12 不同频率下气动力的相对变化比例

Figure 12. Relative change ratio of aerodynamic force at different frequencies

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图 13 不同频率下的时均流场

Figure 13. Time-average flow field at different frequencies

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图 14 不同振动位置下气动力的相对变化比例

Figure 14. Relative change ratio of aerodynamic force at different oscillation locations

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图 15 不同振动位置下的时均流场

Figure 15. Time-average flow field at different oscillation locations

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图 16 未施加振动和施加振动的等效翼型

Figure 16. Equivalent airfoil with and without local oscillation

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图 17 时均压力系数分布的对比

Figure 17. Comparison of time-average pressure coefficient distribution

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图 18 未施加振动和施加振动下的时均无量纲速度场

Figure 18. Time-average non-dimensional velocity field with and without local oscillation

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图 19 翼型局部振动非定常升力系数

Figure 19. Unsteady lift coefficients of airfoil with local oscillation

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图 20 局部振动非定常流场

Figure 20. Unsteady flow field of local oscillation

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图 21 工况1局部振动无量纲涡量云图

Figure 21. Non-dimensional vorticity contours of Case 1 with local oscillation

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图 22 未施加振动和施加振动下的间歇因子分布

Figure 22. γ distributions with and without local oscillation

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图 23 上表面的时均表面摩擦系数的对比

Figure 23. Comparison of time-average skin friction coefficient of upper surface

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表 1 火星和地球大气参数

Table 1. Atmospheric parameters of Mars and Earth

星球	平均大气压力/kPa	大气密度/ (kg·m⁻³)	平均温度/K	大气成分	重力加速度/ (m·s⁻²)	声速/ (m·s⁻¹)	动力黏度/ (kg·m⁻¹·s⁻¹))	摩尔质量/ (g·mol⁻¹)
地球	101.3	1.225	288	N2(77%)，O2(21%)，Ar(0.9%)，CO2(0.03%)	9.8	340	1.789×10⁻⁵	28.966
火星	0.72	0.017	210	CO2(95.3%)，N2(2.7%)，Ar(1.6%)，O2(0.13%)，CO(0.07%)	3.7	227	1.130×10⁻⁵	44.015

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表 2 流场参数

Table 2. Parameters of flow field

工况	翼型弦长/m	来流速度/(m·s⁻¹)	来流攻角/(°)	雷诺数 Re/10⁴	马赫数 Ma	湍流强度/%
工况1	0.1	99.3	6	1.5	0.43	0.082
工况2	0.068	146.9	6	1.5	0.63	0.082

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表 3 网格参数

Table 3. Parameters of meshes

网格	总单元数	翼型表面节点数	翼型到远场节点数
网格A	85 000	601	101
网格B	131 000	801	126
网格C	195 000	1001	151

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表 4 工况1不同振幅下的气动力系数

Table 4. Aerodynamic force coefficients at different amplitudes of Case 1

无量纲振幅A	升力系数C_L	阻力系数C_D	升阻比 L/D
0	0.966 6	0.066 08	14.627
0.001 0	0.999 9	0.070 51	14.181
0.002 5	1.077 5	0.059 74	18.036
0.005 0	1.110 7	0.061 00	18.209
0.007 5	1.102 9	0.063 40	17.395
0.010 0	1.077 2	0.065 72	16.391

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表 5 工况2不同振幅下的气动力系数

Table 5. Aerodynamic force coefficients at different amplitudes of Case 2

无量纲振幅A	升力系数C_L	阻力系数C_D	升阻比 L/D
0	0.834 9	0.072 66	11.491
0.001 0	1.016 0	0.083 80	12.124
0.002 5	1.245 5	0.087 94	14.164
0.005 0	1.278 9	0.076 64	16.686
0.007 5	1.260 4	0.075 68	16.655
0.010 0	1.228 4	0.077 54	15.843

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表 6 工况1不同频率下的气动力系数

Table 6. Aerodynamic force coefficients at different frequencies of Case 1

无量纲频率 f	升力系数C_L	阻力系数C_D	升阻比 L/D
0	0.966 6	0.066 08	14.627
0.50	1.096 8	0.061 67	17.785
0.75	1.088 0	0.059 64	18.243
1.00	1.110 7	0.061 00	18.209
1.50	1.091 6	0.061 64	17.710
2.00	1.052 0	0.060 14	17.493

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表 7 工况2不同频率下的气动力系数

Table 7. Aerodynamic force coefficients at different frequencies of Case 2

无量纲振幅A	升力系数C_L	阻力系数C_D	升阻比 L/D
0	0.834 9	0.072 66	11.491
0.50	1.183 9	0.093 97	12.598
0.75	1.257 2	0.082 09	15.314
1.00	1.278 9	0.076 64	16.686
1.50	1.319 2	0.075 52	17.469
2.00	1.244 7	0.072 06	17.272

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表 8 工况1不同振动位置下的气动力系数

Table 8. Aerodynamic force coefficients at different oscillation locations of Case 1

振动位置起始点	升力系数C_L	阻力系数C_D	升阻比L/D
0c	1.110 7	0.061 00	18.209 2
0.1c	1.059 6	0.066 09	16.033 8
0.2c	1.032 6	0.067 32	15.337 3
0.3c	0.998 2	0.068 75	14.519 9
0.4c	0.995 0	0.071 47	13.921 7

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表 9 工况2不同振动位置下的气动力系数

Table 9. Aerodynamic force coefficients at different oscillation locations of Case 2

振动位置起始点	升力系数C_L	阻力系数C_D	升阻比L/D
0c	1.278 9	0.076 64	16.686 1
0.1c	1.314 9	0.089 68	14.662 1
0.2c	1.137 9	0.097 79	11.636 5
0.3c	1.105 6	0.095 78	11.543 6
0.4c	1.066 1	0.093 20	11.439 4

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参考文献(29)

[1]	赵宇鴳, 周迪圣, 李雄耀, 等. 国际火星探测科学目标演变与未来展望[J]. 科学通报, 2020, 65(23): 2439-2453. doi: 10.1360/TB-2019-0638 ZHAO Y A, ZHOU D S, LI X Y, et al. The evolution of scientific goals for Mars exploration and future prospects[J]. Chinese Science Bulletin, 2020, 65(23): 2439-2453(in Chinese). doi: 10.1360/TB-2019-0638
[2]	赵鹏越, 全齐全, 邓宗全, 等. 旋翼式火星无人机技术发展综述[J]. 宇航学报, 2018, 39(2): 121-130. doi: 10.3873/j.issn.1000-1328.2018.02.002 ZHAO P Y, QUAN Q Q, DENG Z Q, et al. Overview of research on rotary-wing Mars unmanned aerial vehicles[J]. Journal of Astronautics, 2018, 39(2): 121-130(in Chinese). doi: 10.3873/j.issn.1000-1328.2018.02.002
[3]	KONING W J F, JOHNSON W, GRIP H F. Improved Mars helicopter aerodynamic rotor model for comprehensive analyses[J]. AIAA Journal, 2019, 57(9): 3969-3979. doi: 10.2514/1.J058045
[4]	BALARAM J, DAUBAR I J, BAPST J, et al. Helicopters on Mars: Compelling science of extreme terrains enabled by an aerial platform[C]//9th International Conference on Mars, 2019.
[5]	MCMASTERS J, HENDERSON M L. Low-speed single-element airfoil synthesis[J]. Technical Soaring, 1979, 6: 1-21.
[6]	WANG S, ZHOU Y, ALAM M M, et al. Turbulent intensity and Reynolds number effects on an airfoil at low Reynolds numbers[J]. Physics of Fluids, 2014, 26(11): 115107. doi: 10.1063/1.4901969
[7]	GAD-EL-HAK M. Micro-air-vehicles: Can they be controlled better?[J]. Journal of Aircraft, 2001, 38(3): 419-429. doi: 10.2514/2.2807
[8]	ANYOJI M, NUMATA D, NAGAI H, et al. Effects of Mach number and specific heat ratio on low-Reynolds-number airfoil flows[J]. AIAA Journal, 2015, 53(6): 1640-1654. doi: 10.2514/1.J053468
[9]	KONING W J F, JOHNSON W, ALLAN B G. Generation of Mars helicopter rotor model for comprehensive analyses[C]//Proceedings of the AHS International Technical Meeting on Aeromechanics Design for Transformative Vertical Flight, 2018.
[10]	张旺龙, 谭俊杰, 陈志华, 等. 抽吸控制对低雷诺数下翼型分离流动的影响[J]. 航空学报, 2014, 35(1): 141-150. ZHANG W L, TAN J J, CHEN Z H, et al. Effect of suction control on separation flow around an airfoil at low Reynolds numbers[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 141-150(in Chinese).
[11]	左伟, 顾蕴松, 王奇特, 等. 低雷诺数下机翼气动特性研究及控制[J]. 航空学报, 2016, 37(4): 1139-1147. ZUO W, GU Y S, WANG Q T, et al. Aerodynamic characteristics and flow control on a rectangular wing at low Reynolds number[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(4): 1139-1147(in Chinese).
[12]	孟宣市, 杨泽人, 陈琦, 等. 低雷诺数下层流分离的等离子体控制[J]. 航空学报, 2016, 37(7): 2112-2122. MENG X S, YANG Z R, CHEN Q, et al. Laminar separation control at low Reynolds numbers using plasma actuation[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(7): 2112-2122(in Chinese).
[13]	SINHA S K. Flow separation control with microflexural wall vibrations[J]. Journal of Aircraft, 2001, 38(3): 496-503. doi: 10.2514/2.2789
[14]	SINHA S. Aircraft drag reduction with flexible composite surface boundary layer control[C]// Proceedings of the 2nd AIAA Flow Control Conference. Reston: AIAA, 2004.
[15]	ARTHUR G G, MCKEON B J, DEARING S S, et al. Manufacture of micro-sensors and actuators for flow control[J]. Microelectronic Engineering, 2006, 83(4-9): 1205-1208. doi: 10.1016/j.mee.2006.01.171
[16]	WEDDLE A, ZAREMSKI S, ZHANG L, et al. Control of laminar separation bubble using electro-active polymers[C]// Proceedings of the 6th AIAA Flow Control Conference. Reston: AIAA, 2012.
[17]	DEMAURO E P, DELL’ORSO H, ZAREMSKI S, et al. Control of laminar separation bubble on NACA 0009 airfoil using electroactive polymers[J]. AIAA Journal, 2015, 53(8): 2270-2279. doi: 10.2514/1.J053670
[18]	卢丛玲, 祁浩天, 徐国华. 共轴双旋翼非定常流场干扰特性[J]. 航空动力学报, 2019, 34(7): 1459-1470. LU C L, QI H T, XU G H. Unsteady flow field interaction of coaxial rotor[J]. Journal of Aerospace Power, 2019, 34(7): 1459-1470(in Chinese).
[19]	KANG W, LEI P F, ZHANG J Z, et al. Effects of local oscillation of airfoil surface on lift enhancement at low Reynolds number[J]. Journal of Fluids and Structures, 2015, 57: 49-65. doi: 10.1016/j.jfluidstructs.2015.05.009
[20]	DI G Q, WU Z C, HUANG D G. The research on active flow control method with vibration diaphragm on a NACA0012 airfoil at different stalled angles of attack[J]. Aerospace Science and Technology, 2017, 69: 76-86. doi: 10.1016/j.ast.2017.06.020
[21]	LOU B, YE S J, WANG G F, et al. Numerical and experimental research of flow control on an NACA 0012 airfoil by local vibration[J]. Applied Mathematics and Mechanics, 2019, 40(1): 1-12. doi: 10.1007/s10483-019-2404-8
[22]	刘强, 刘周, 白鹏, 等. 低雷诺数翼型蒙皮主动振动气动特性及流场结构数值研究[J]. 力学学报, 2016, 48(2): 269-277. LIU Q, LIU Z, BAI P, et al. Numerical study about aerodynamic characteristics and flow field structures for a skin of airfoil with active oscillation at low Reynolds number[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(2): 269-277(in Chinese).
[23]	李冠雄, 马东立, 杨穆清, 等. 低雷诺数翼型局部振动非定常气动特性[J]. 航空学报, 2018, 39(1): 121427. LI G X, MA D L, YANG M Q, et al. Unsteady aerodynamic characteristics of airfoil with local oscillation at low Reynolds number[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(1): 121427(in Chinese).
[24]	杨荣菲, 徐堃, 仲冬冬, 等. 振动凸包控制低雷诺数高负荷低压涡轮叶栅层流分离的数值研究[J]. 推进技术, 2019, 40(2): 267-275. doi: 10.13675/j.cnki.tjjs.170805 YANG R F, XU K, ZHONG D D, et al. Numerical study on laminar separation control using dynamic hump in high-loaded low pressure turbine cascade at low-Reynolds number[J]. Journal of Propulsion Technology, 2019, 40(2): 267-275(in Chinese). doi: 10.13675/j.cnki.tjjs.170805
[25]	LEI J M, ZHANG J W, NIU J P. Effect of active oscillation of local surface on the performance of low Reynolds number airfoil[J]. Aerospace Science and Technology, 2020, 99: 105774. doi: 10.1016/j.ast.2020.105774
[26]	MENTER F R, LANGTRY R B, LIKKI S R, et al. A correlation-based transition model using local variables—Part I: Model formulation[J]. Journal of Turbomachinery, 2006, 128(3): 413. doi: 10.1115/1.2184352
[27]	SUWA T, NOSE K, NUMATA D, et al. Compressibility effects on airfoil aerodynamics at low Reynolds number[C]// Proceedings of the 30th AIAA Applied Aerodynamics Conference. Reston: AIAA, 2012.
[28]	吴锤结, 解妍琼, 吴介之. "流体滚动轴承"效应及其在流动控制中的应用[C]//全国第九届分离流、旋涡和流动控制会议. 北京: 中国空气动力学会, 2002: 281-290 WU C J, XIE Y Q, WU J Z. Effect and application of flow control of fluid ball bearing[C]//The Ninth National Conference on Flow Separation, Vortex and Flow Control Conference. Beijing: CARS, 2002: 281-290 (in Chinese).
[29]	吴锤结, 王亮. 运动物面流动控制[J]. 固体力学学报, 2005, 26: 10-21. WU C J, WANG L. Control flow of moving interface[J]. Acta Mechanica Solida Sinica, 2005, 26: 10-21(in Chinese).