Optimization of lift-to-drag characteristics for high-speed wing-in-ground effect based on the Kriging model
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摘要:
为了提高高速地效飞行器的气动性能，采用基于Kriging模型的全局气动优化方法，以升阻比为优化目标，在
Ma =0.2，0.3，0.5和0.8工况下对地效飞行器的翼型进行优化研究。结果表明：地效优化翼型气动性能的改善主要来自两方面。一方面是地面效应带来的改善，当Ma ≤0.5时，地效翼型升阻比的提升主要是源于阻力的减小，当Ma =0.8时，地效翼型升阻比的提升主要由于升力的增大。地面效应使得翼型的升阻比相较于非地效翼型分别提高31.6%、55.0%、101%和31.1%。另一方面是几何外形优化带来的改善，随着来流马赫数的增大，优化后的翼型前缘半径减小，最大弯度位置后移，翼型的厚度减小，优化翼型的升阻比相较于原NACA4512翼型分别提升了12.8%、13.03%、7.45%、38.3%。对优化翼型的气动性能分析可知，翼型的升阻比随离地高度的减小而增大，随迎角的增大先增大后减小。但在高亚声速低迎角工况下，翼型离地面的距离过小，会使得翼型的下表面形成激波，升阻比减小。Abstract:In order to improve the aerodynamic performance of high-speed wing-in-ground effect vehicle, the global aerodynamic optimization method based on the Kriging model was adopted. The optimization of wing-in-ground effect at
Ma =0.2,Ma =0.3,Ma =0.5 andMa =0.8 was carried out with the aim of increasing the lift-drag ratio. The aerodynamic performance improvement included two aspects. One was from the ground effect, the drag force reduction atMa ≤0.5, and lift force increase atMa =0.8. The increase of 31.6%, 55.0%, 101% and 31.1% in lift-drag ratio by the ground effect was achieved compared with these cases without the ground effect. The other one was from the configuration optimization. With the increase of Ma, the leading-edge radius of the optimized airfoil decreased, the maximum bending position moved downstream, the airfoil thickness decreased and thus the lift-drag ratio of the optimized airfoil increased by 12.8%, 13.03%, 7.45% and 38.3% when compared with the lift-drag ratio of original NACA4512 airfoil. The aerodynamic performance of the optimized airfoil showed that the lift-to-drag ratio of the airfoil increased with the decrease of ground clearance, with the increase of the angle of attack the lift-to-drag ratio increased first and then decreased, but under the condition of high subsonic speed and low angle of attack, the airfoil was too close to the ground, a shock wave was formed on the lower surface of the airfoil, which resulted in the decrease of the lift-to-drag ratio of the airfoil. -
图 3 地效优化翼型升阻比增益概念示意图
Figure 3. Schematic diagram of lift-to-drag ratio gain of the optimized ground effect airfoil
图 4 优化翼型和NACA4512翼型气动外形对比
Figure 4. Comparison of aerodynamic shapes between optimized airfoils and NACA4512 airfoil
图 5 地面效应增益和气动优化增益的占比柱状图
Figure 5. Histogram of ground effect gain and aerodynamic optimization gain
图 6 Ma=0.2时优化翼型和NACA4512翼型的压力系数分布图
Figure 6. Pressure coefficient distribution for optimized airfoils and NACA4512 airfoil when Ma=0.2
图 7 Ma=0.3时优化翼型和NACA4512翼型的压力系数分布图
Figure 7. Pressure coefficient distribution for optimized airfoil and NACA4512 airfoil when Ma=0.3
图 8 Ma=0.2时优化翼型和NACA4512翼型的马赫数分布云图
Figure 8. Mach number clouds for optimized airfoils and NACA4512 airfoil when Ma=0.2
图 9 Ma=0.3时优化翼型和NACA4512翼型的马赫数分布云图
Figure 9. Mach number clouds for optimized airfoil and NACA4512 airfoil when Ma=0.3
图 10 Ma=0.3时NACA4512翼型在地效和非地效工况下的滞止流线图
Figure 10. Stagnation streamline of NACA4512 airfoil under ground effect and non-ground effect when Ma=0.3
图 11 Ma=0.5时优化翼型和NACA4512翼型的压力系数分布图
Figure 11. Pressure coefficient distribution for optimized airfoil and NACA4512 airfoil when Ma=0.5
图 12 Ma=0.5时优化翼型和NACA4512翼型的马赫数分布云图
Figure 12. Mach number clouds for optimized airfoil and NACA4512 airfoil when Ma=0.5
图 13 Ma=0.5时NACA4512翼型在地效和非地效工况下的滞止点示意图
Figure 13. Stagnation point of airfoil under ground effect and non-ground effect when Ma=0.5
图 14 Ma=0.8时优化翼型和NACA4512翼型的压力系数分布图
Figure 14. Pressure coefficient distribution for optimized airfoils and NACA4512 airfoil when Ma=0.8
图 15 Ma=0.8时优化翼型和NACA4512翼型的马赫数分布云图
Figure 15. Mach number clouds for optimized airfoils and NACA4512 airfoil when Ma=0.8
图 16 Ma=0.8时NACA4512翼型在地效和非地效工况下的滞止流线图
Figure 16. Stagnation streamline of NACA4512 airfoil under ground effect and non-ground effect when Ma=0.8
图 17 不同来流攻角下翼型阻力系数随离地高度的变化
Figure 17. Variation of wing drag coefficient with ground clearance at different attack angles of incoming flow
图 18 不同来流攻角下翼型升力系数随离地高度的变化
Figure 18. Variation of wing lift coefficient with ground clearance at different attack angles of incoming flow
图 19 不同来流攻角下翼型升阻比随离地高度的变化
Figure 19. Variation of wing lift-drag ratio coefficient with ground clearance at different attack angles of incoming flow
图 20 Ma =0.8, α=0°时不同离地高度下翼型马赫数分布云图
Figure 20. Mach number clouds for airfoil with different ground clearances when Ma=0.8, α=0°
表 1 优化翼型和NACA4512翼型气动参数对比
Table 1. Comparison of aerodynamic parameters between optimized airfoils and NACA4512 airfoil
Ma 翼型 升力系数 阻力系数 升阻比 0.2 NACA4512（非地效） 1.326 0.0160 82.9 NACA4512（地效） 1.341 0.0123 109.0 （η1=31.6%） OPT1（地效） 1.400 0.0114 123.0 （η2=12.8%） 0.3 NACA4512（非地效） 1.377 0.0183 75.3 NACA4512（地效） 1.376 0.0118 116.6 （η1=55.0%） OPT2（地效） 1.450 0.0110 131.8 （η2=13.0%） 0.5 NACA4512（非地效） 1.537 0.0214 71.8 NACA4512（地效） 1.506 0.0115 134 （η1=101%） OPT3（地效） 1.587 0.0110 144 （η2=7.45%） 0.8 NACA4512（非地效） 0.948 0.157 6.04 NACA4512（地效） 1.393 0.176 7.91 （η1=31.1%） OPT4（地效） 1.549 0.141 10.99 （η2=38.3%） 
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[1] HALLORAN M, O’MEARA S. Wing in ground effect craft review[M]. Australia: DSTO Aeronautical and Maritime Research Laboratory, 1999. [2] FROLOV V. Ground effect on lift of thick wing airfoil[C]//2017 International Conference on Mechanical, System and Control Engineering. Piscataway, US: IEEE, 2017: 319-322. [3] HE Yilei, QU Qiulin, AGARWAL R K. Shape optimization of an airfoil in ground effect for application to WIG craft[J]. Journal of Aerodynamics, 2014, 2014(1): 931232. [4] HU Huan, ZHANG Guiyong, LI Daochun, et al. Shape optimization of airfoil in ground effect based on free-form deformation utilizing sensitivity analysis and surrogate model of artificial neural network[J]. Ocean Engineering, 2022, 257: 111514. doi: 10.1016/j.oceaneng.2022.111514 [5] DOIG G, BARBER T J, NEELY A J, et al. Aerodynamics of an aerofoil in transonic ground effect: numerical study at full-scale Reynolds numbers[J]. The Aeronautical Journal, 2012, 116(1178): 407-430. doi: 10.1017/S0001924000005297 [6] 刘浩, 孙建红, 张延泰, 等. 地面效应下的不同翼型亚声速气动特性分析[J]. 南京航空航天大学学报, 2020, 52(3): 408-415. LIU Hao, SUN Jianhong, ZHANG Yantai, et al. Aerodynamic characteristics of different air-foil in subsonic flow with ground effect[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2020, 52(3): 408-415. (in chineseLIU Hao, SUN Jianhong, ZHANG Yantai, et al. Aerodynamic characteristics of different air-foil in subsonic flow with ground effect[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2020, 52(3): 408-415. (in chinese) [7] 刘浩, 孙建红, 孙智, 等. 波浪条件下地效翼型气动力的环量控制研究[J]. 上海交通大学学报, 2022, 56(8): 1101-1110. LIU Hao, SUN Jianhong, SUN Zhi, et al. Circulation control of airfoil aerodynamic force under ground effect of wavy wall[J]. Journal of Shanghai Jiao Tong University, 2022, 56(8): 1101-1110. (in ChineseLIU Hao, SUN Jianhong, SUN Zhi, et al. Circulation control of airfoil aerodynamic force under ground effect of wavy wall[J]. Journal of Shanghai Jiao Tong University, 2022, 56(8): 1101-1110. (in Chinese) [8] 韩瀚, 项昌乐, 徐彬. 共轴反桨涵道式推进单元地面效应气动性能[J]. 航空动力学报, 2019, 34(7): 1440-1449. HAN Han, XIANG Changle, XU Bin. Aerodynamic performance of shrouded coaxial anti-rotating rotor propulsion unit with ground effect[J]. Journal of Aerospace Power, 2019, 34(7): 1440-1449. (in ChineseHAN Han, XIANG Changle, XU Bin. Aerodynamic performance of shrouded coaxial anti-rotating rotor propulsion unit with ground effect[J]. Journal of Aerospace Power, 2019, 34(7): 1440-1449. (in Chinese) [9] 屠秋野, 王晓峰, 沈鸿萃, 等. 地效翼船用涵道螺旋桨的设计试验[J]. 航空动力学报, 2004, 19(6): 798-801. TU Qiuye, WANG Xiaofeng, SHEN Hongcui, et al. The duct fan design and test for WIG craft[J]. Journal of Aerospace Power, 2004, 19(6): 798-801. (in Chinese doi: 10.3969/j.issn.1000-8055.2004.06.011TU Qiuye, WANG Xiaofeng, SHEN Hongcui, et al. The duct fan design and test for WIG craft[J]. Journal of Aerospace Power, 2004, 19(6): 798-801. (in Chinese) doi: 10.3969/j.issn.1000-8055.2004.06.011 [10] QU Qiulin, JIA Xi, WANG Wei, et al. Numerical study of the aerodynamics of a NACA 4412 airfoil in dynamic ground effect[J]. Aerospace Science and Technology, 2014, 38: 56-63. doi: 10.1016/j.ast.2014.07.016 [11] 高正红, 王超. 飞行器气动外形设计方法研究与进展[J]. 空气动力学学报, 2017, 35(4): 516-528, 454. GAO Zhenghong, WANG Chao. Aerodynamic shape design methods for aircraft: status and trends[J]. Acta Aerodynamica Sinica, 2017, 35(4): 516-528, 454. (in Chinese doi: 10.7638/kqdlxxb-2017.0058GAO Zhenghong, WANG Chao. Aerodynamic shape design methods for aircraft: status and trends[J]. Acta Aerodynamica Sinica, 2017, 35(4): 516-528, 454. (in Chinese) doi: 10.7638/kqdlxxb-2017.0058 [12] FORRESTER A I J, KEANE A J. Recent advances in surrogate-based optimization[J]. Progress in Aerospace Sciences, 2009, 45(1/2/3): 50-79. [13] SIMPSON T W, BOOKER A J, GHOSH D, et al. Approximation methods in multidisciplinary analysis and optimization: a panel discussion[J]. Structural and Multidisciplinary Optimization, 2004, 27(5): 302-313. [14] 韩忠华. Kriging模型及代理优化算法研究进展[J]. 航空学报, 2016, 37(11): 3197-3225. HAN Zhonghua. Kriging surrogate model and its application to design optimization: a review of recent progress[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3197-3225. (in ChineseHAN Zhonghua. Kriging surrogate model and its application to design optimization: a review of recent progress[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3197-3225. (in Chinese) [15] 苏伟, 高正红, 夏露. 一种代理遗传算法及其在气动优化设计中的应用[J]. 西北工业大学学报, 2008, 26(3): 303-307. SU Wei, GAO Zhenghong, XIA Lu. An effective surrogate-assisted genetic algorithm for airfoil aerodynamic optimization design[J]. Journal of Northwestern Polytechnical University, 2008, 26(3): 303-307. (in Chinese doi: 10.3969/j.issn.1000-2758.2008.03.007SU Wei, GAO Zhenghong, XIA Lu. An effective surrogate-assisted genetic algorithm for airfoil aerodynamic optimization design[J]. Journal of Northwestern Polytechnical University, 2008, 26(3): 303-307. (in Chinese) doi: 10.3969/j.issn.1000-2758.2008.03.007 [16] 韩忠华, 许晨舟, 乔建领, 等. 基于代理模型的高效全局气动优化设计方法研究进展[J]. 航空学报, 2020, 41(5): 623344. HAN Zhonghua, XU Chenzhou, QIAO Jianling, et al. Recent progress of efficient global aerodynamic shape optimization using surrogate-based approach[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(5): 623344. (in ChineseHAN Zhonghua, XU Chenzhou, QIAO Jianling, et al. Recent progress of efficient global aerodynamic shape optimization using surrogate-based approach[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(5): 623344. (in Chinese) [17] KULFAN B, BUSSOLETTI J. “Fundamental” parameteric geometry representations for aircraft component shapes[C]//11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Portsmouth, Virginia: AIAA, 2006. [18] 关晓辉, 李占科, 宋笔锋. CST气动外形参数化方法研究[J]. 航空学报, 2012, 33(4): 625-633. GUAN Xiaohui, LI Zhanke, SONG Bifeng. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 625-633. (in ChineseGUAN Xiaohui, LI Zhanke, SONG Bifeng. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 625-633. (in Chinese) -
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