高超声速飞行器宽速域翼型/机翼设计与分析

doi:10.7527/S1000-6893.2018.21737

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

高超声速飞行器宽速域翼型/机翼设计与分析

孙祥程, 韩忠华, 柳斐, 宋科, 宋文萍

西北工业大学航空学院翼型叶栅空气动力学国家级重点实验室, 西安 710072

收稿日期:2017-09-11 修回日期:2018-01-24 出版日期:2018-06-15 发布日期:2018-01-24
通讯作者: 韩忠华,E-mail:hanzh@nwpu.edu.cn E-mail:hanzh@nwpu.edu.cn
基金资助:
国家自然科学基金（11272265）；航空科学基金（2016ZA53011）

Design and analysis of hypersonic vehicle airfoil/wing at wide-range Mach numbers

SUN Xiangcheng, HAN Zhonghua, LIU Fei, SONG Ke, SONG Wenping

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2017-09-11 Revised:2018-01-24 Online:2018-06-15 Published:2018-01-24
Supported by:
National Natural Science Foundation of China (11272265); Aeronautical Science Foundation of China (2016ZA53011)

摘要/Abstract

摘要： 对于现代高超声速飞行器的设计而言，除了需要保证高超声速的性能外，还必须兼顾满足工程需求的亚跨超声速特性。首先，采用雷诺平均Navier-Stokes（RANS）方程流动求解器，结合基于Kriging模型的代理优化算法，开展了高超声速飞行器宽速域翼型的优化设计研究，设计出了一种下表面具有双"S"形特征的新翼型。综合性能评估结果表明，该翼型相比于常规的高超声速翼型，在跨声速和高超声速下具有更加优良的气动特性；其跨声速状态下的升阻比达到78.9，高超声速状态下的升阻比达到5.94，能够实现宽速域内良好的综合气动性能。其次，开展了仿德国"桑格尔号"（SANGER）空天飞机运载机机翼的气动特性研究，对配置宽速域翼型与常规高超声速翼型的机翼进行了气动力特性综合对比分析。结果表明，配置新翼型的机翼在宽速域范围内整体气动性能更优，说明所设计的宽速域翼型在三维机翼上也具有一定的实用价值。

关键词: 翼型设计, 气动优化设计, 高超声速飞行器, 计算流体力学, 宽速域

Abstract: The study of wider-range Mach number configuration is of great importance for the development of hypersonic vehicles. This study is aimed at designing a wider-range Mach number airfoil based on Reynolds-Averaged Navier-Stokes (RANS) equations and the surrogate-based optimization method based on kriging model. An airfoil with a lower surface of double "S" shape is designed. The aerodynamic characteristics of the designed airfoil are compared with quadrilateral and hexagon airfoils. Results show that the lift-to-drag ratio of the new airfoil is as large as 78.9 in transonic flow, and the lift-drag ratio reaches 5.94 in hypersonic flow. The aerodynamic characteristics of SANGER wing with the new airfoil is compared with that of the wing with quadrilateral and hexagon airfoils. In a word, the new airfoil as well as the wing with the new airfoil can achieve good overall aerodynamic performance at a wider-range Mach numbers, and is supposed to be applied to the design of the wider-range Mach number airfoil/wing for hypersonic vehicle applications.

Key words: airfoil design, aerodynamic optimization design, hypersonic vehicle, computational fluid dynamics, wide-range Mach numbers

中图分类号:

V211.3

孙祥程, 韩忠华, 柳斐, 宋科, 宋文萍. 高超声速飞行器宽速域翼型/机翼设计与分析[J]. 航空学报, 2018, 39(6): 121737-121737.

SUN Xiangcheng, HAN Zhonghua, LIU Fei, SONG Ke, SONG Wenping. Design and analysis of hypersonic vehicle airfoil/wing at wide-range Mach numbers[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(6): 121737-121737.

参考文献

[1] 吴子牛, 白晨媛, 李娟. 高超声速飞行器流动特征分析[J]. 航空学报, 2015, 36(1):63-90. WU Z N, BAI C Y, LI J. Analysis of flow characteristics for hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):63-90(in Chinese).
[2] 罗金玲, 李超, 徐锦. 高超声速飞行器机体/推进一体化设计的启示[J]. 航空学报, 2015, 36(1):39-48. LUO J L, LI C, XU J. Inspiration of hypersonic vehicle with airframe/propulsion integrated design[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):39-48(in Chinese).
[3] 曹长强, 蔡晋生, 段焰辉. 超声速翼型气动优化设计[J]. 航空学报, 2015, 36(12):21-31. CAO C Q, CAI J S, DUAN Y H. Aerodynamic design optimization of supersonic airfoils[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(12):21-31(in Chinese).
[4] UENO A, SUZUKI K. CFD-based shape optimization of hypersonic vehicles considering transonic aerodynamic performance:AIAA-2008-288[R]. Reston, VA:AIAA, 2008.
[5] HAN Z H, HE F, SONG W P, et al. A preconditioned multigrid method for efficient simulation of three-dimensional compressible and incompressible flows[J]. Chinese Journal of Aeronautics, 2007, 20(4):289-296.
[6] XIE F, SONG W P, HAN Z H. Numerical study of high-resolution scheme based on preconditioning method[J]. Journal of Aircraft, 2009, 46(2):520-525.
[7] 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 Z H. 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).
[8] HAN Z H. SURROOPT:A generic surrogate-based optimization code for aerodynamic and multidisciplinary design[C]//30th Congress of the International Council of the Aeronautical Sciences, 2016.
[9] LIU J, SONG W P, HAN Z H, et al. Efficient aerodynamic shape optimization of transonic wings using a parallel infilling strategy and surrogate models[J]. Structural and Multidisciplinary Optimization, 2016, 55(3):925-943.
[10] SPALART P, ALLMARAS S. A one-equation turbulence model for aerodynamic flows[J]. La Recherche Aérospatiale, 2003, 439(1):5-21.
[11] 韩忠华. 旋翼绕流的高效数值计算方法及主动流动控制研究[D]. 西安:西北工业大学,2007. HAN Z H. Efficient method for simulation of viscous flows past helicopter rotors and active flow control[D]. Xi'an:Northwestern Polytechnical University, 2007(in Chinese).
[12] KULFAN B M, BUSSOLETTI J E. Fundamental parametric geometry representations for aircraft component shapes:AIAA-2006-6948[R]. Reston, VA:AIAA, 2006.
[13] KULFAN B M. A universal parametric geometry representation method-"CST":AIAA-2007-0062[R]. Reston, VA:AIAA, 2007.
[14] COOK P H,MCDONALD M A,FIRMIN M C P. Aerofoil RAE2822-Pressure distributions, and boundary layer and wake measurements:AGARD AR 138[R]. Paris:AGARD, 1979
[15] WILCOX F, BIRCH T, ALLEN J. Force, surface pressure, and flowfield measurements on a slender missile configuration with square cross-section at supersonic speeds[C]//22nd Applied Aerodynamics Conference and Exhibit, 2004.
[16] WEINGERTNER S. SAENGER-The reference concept of the German hypersonics technology program:AIAA-1993-5161[R]. Reston,VA:AIAA, 1993.
[17] KUCZERA H, SACHER P, KRAMMER P. The German hypersonics programme-status report:AIAA-1991-5001[R]. Reston,VA:AIAA, 1991.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速飞行器宽速域翼型/机翼设计与分析

Design and analysis of hypersonic vehicle airfoil/wing at wide-range Mach numbers

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	刘琦, 史勇杰, 胡志远, 徐国华. 共轴刚性旋翼气动及噪声特性的参数影响分析[J]. 航空学报, 2024, 45(9): 528856-528856.
[2]	王雪鹤, 柴春硕, 邢世龙, 樊枫, 黄水林. 共轴高速直升机反流区翼型设计及减阻机理[J]. 航空学报, 2024, 45(9): 529960-529960.
[3]	陈树生, 冯聪, 张兆康, 赵轲, 张新洋, 高正红. 基于全局/梯度优化方法的宽速域乘波-机翼布局气动设计[J]. 航空学报, 2024, 45(6): 629596-629596.
[4]	杨博, 于贺, 樊子辰. 微观能量分析气动光学效应时变误差的方法[J]. 航空学报, 2024, 45(4): 128703-128703.
[5]	纪鉴恒, 蔡尊, 王泰宇, 孙明波, 王振国. 宽速域超燃冲压发动机流动燃烧过程研究进展[J]. 航空学报, 2024, 45(3): 28696-028696.
[6]	陆凤霞, 韦坤, 王春雷, 鲍和云, 朱如鹏. 直升机中减三相流金属屑末可达性[J]. 航空学报, 2024, 45(1): 128524-128524.
[7]	倪炜霖, 王永海, 徐聪, 赤丰华, 梁海朝. 基于强化学习的高超飞行器协同博弈制导方法[J]. 航空学报, 2023, 44(S2): 729400-729400.
[8]	马平, 张宁, 石安华, 于哲峰, 梁世昌, 黄洁. 典型微波波段信号在模拟等离子体中的传输特性[J]. 航空学报, 2023, 44(S2): 729476-729476.
[9]	陈浩宇, 王彬文, 宋巧治, 李晓东. 热颤振地面模拟试验技术[J]. 航空学报, 2023, 44(8): 227295-227295.
[10]	任炯, 王刚, 胡国栋, 石晓露. 自适应Walsh函数有限体积方法[J]. 航空学报, 2023, 44(8): 127444-127444.
[11]	马印锴, 李祝飞, 黄琪, 杨基明. 宽速域翼尖涡及其与斜激波相互作用[J]. 航空学报, 2023, 44(7): 38-50.
[12]	曹文博, 刘溢浪, 张伟伟. 基于降阶模型和梯度优化的流场加速收敛方法[J]. 航空学报, 2023, 44(6): 127090-127090.
[13]	王梓伊, 张伟伟, 刘磊, 杨肖峰. 适用于复杂流动的热气动弹性降阶建模方法[J]. 航空学报, 2023, 44(4): 126807-126807.
[14]	刘超宇, 屈峰, 孙迪, 刘传振, 钱战森, 白俊强. 基于离散伴随的高超声速密切锥乘波体气动优化设计[J]. 航空学报, 2023, 44(4): 126664-126664.
[15]	韩荣, 刘伟, 杨小亮. 高超声速飞行器自适应减阻盘动态减阻机理[J]. 航空学报, 2023, 44(4): 126633-126633.