高压捕获翼双翼构型宽速域气动性能研究

肖尧; 崔凯; 李广利; 田中伟; 常思源

doi:10.19527/j.cnki.2096-1642.1049

高压捕获翼双翼构型宽速域气动性能研究

doi: 10.19527/j.cnki.2096-1642.1049

肖尧^{1, 2,},
崔凯^{1, 2},
李广利^{1, 2},
田中伟³,
常思源¹

1.
中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190
2.
中国科学院大学工程科学学院, 北京 100049
3.
中国科学院力学研究所宽域飞行工程科学与应用中心, 北京 100190

基金项目:

国家自然科学基金 12002347

中国科学院基础前沿科学研究计划 ZDBS-LY-JSC005

详细信息

作者简介:
肖尧(1988-)男, 博士, 工程师, 主要研究方向为宽域高超飞行器气动布局设计与优化。E-mail: xiaoyao@imech.ac.cn

中图分类号: V221+.3
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- 被引次数: 0
出版历程
- 收稿日期: 2023-04-07
- 修回日期: 2023-04-20

Research on Aerodynamic Performance of High-Pressure Capturing Wing with Bi-Wing Configuration in Wide-Speed Range

XIAO Yao^{1, 2
,},
CUI Kai^{1, 2},
LI Guang-li^{1, 2},
TIAN Zhong-wei³,
CHANG Si-yuan¹

1.
State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
2.
School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049, China
3.
Wide Field Flight Engineering Science and Application Center, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

摘要

摘要: 宽域高超飞行器气动布局设计已是研究热点之一。高压捕获翼新型气动布局可同时满足高容积率、高升力和高升阻比, 此布局前期研究主要针对高超声速状态。基于该背景, 以宽域高超飞行器为主要目标, 依据高压捕获翼基本设计原理, 发展了一种新型双翼构型。对该构型的宽速域气动特性研究结果表明, 在亚声速条件下添加捕获翼可使飞行器升力系数提高约16.6%, 在跨声速区域捕获翼可抑制飞行器气动焦点跳变, 飞行器在全速域范围内均为纵向静稳定。
- 高压捕获翼 /
- 宽域飞行器 /
- 双翼构型 /
- 气动特性 /
- 计算流体力学
Abstract: The aerodynamic configuration design of wide-range hypersonic vehicle has become one of the research hotspots. The new aerodynamic configuration of high-pressure capturing wing (HCW) can meet the requirements of high volume ra-tio, high lift and high lift-to-drag ratio at the same time. The preliminary research of this configuration is mainly aimed at the hypersonic state. Based on this background, this paper took the wide-range hypersonic vehicle as the main target and developed a new bi-wing configuration according to the basic design principle of HCW. The research results show that the lift coefficient of the vehicle can be increased by about 16.6% when the capturing wing is added in the subsonic range. Furthermore, the capturing wing can suppress the jump of the aerodynamic focus of the vehicle in the transonic range, and the vehicle is statically stable in the wide-speed range.
- high-pressure capturing wing /
- wide-range aircraft /
- bi-wing configuration /
- aerodynamic performance /
- computational fluid dynamics

HTML全文

图 1 高压捕获翼设计原理

Figure 1. Design principle of the high-pressure capturing wing

下载: 全尺寸图片幻灯片

图 2 高压捕获翼双翼构型及参考构型示意图

Figure 2. Illustration of the bi-wing configuration and the reference configuration of high-pressure capturing wing

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图 3 构型计算网格

Figure 3. Computational grid of configuration

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图 4 Ma=6工况压力分布云图

Figure 4. Pressure contours under Ma=6 condition

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图 5 Ma=6工况气动性能

Figure 5. Aerodynamic performance under Ma=6 condition

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图 6 Ma=0.5工况压力分布云图及流场涡结构

Figure 6. Pressure contour and vortex structures under Ma=0.5 condition

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图 7 俯仰力矩系数-升力系数曲线

Figure 7. Pitch moment-lift coefficient curves

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图 8 气动焦点随Mach数变化曲线

Figure 8. Aerodynamic focus with Mach number

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图 9 Ma=0.8, AoA=10°工况对称面压力分布云图

Figure 9. Pressure contours on the symmetric plane at Ma=0.8 AoA=5° condition

下载: 全尺寸图片幻灯片

表 1 计算工况

Table 1. Simulation conditions

case	Ma	H/km	AoA/(°)
1	0.3	0	-5, 0, 5, 10, 15, 20, 25
2	0.5	2
3	0.8	3
4	1.2	4
5	2	8
6	4	20
7	6	30

下载: 导出CSV

表 2 亚声速工况升力系数

Table 2. Lift coefficient under subsonic conditions

Ma	configuration	C_L
Ma	configuration	AoA=5°	AoA=10°	AoA=15°	AoA=20°
0.3	HCW	0.052 6	0.299 8	0.575 8	0.837 2
	HCW-Ref	0.055 8	0.257 2	0.503 5	0.747 0
		-5.8%	16.6%	14.4%	12.1%
0.5	HCW	0.054 5	0.307 38	0.589 82	0.855 32
	HCW-Ref	0.057 14	0.263 82	0.517 16	0.769 18
		-4.6%	16.5%	14.0%	11.2%

下载: 导出CSV

参考文献(22)

[1]	蔡国飙, 徐大军. 高超声速飞行器技术[M]. 北京: 科学出版社, 2012. Cai G B, Xu D J. Technology of hypersonic vehicle[M]. Beijing: Science Press, 2012(in Chinese).
[2]	李宪开, 王霄, 柳军, 等. 水平起降高超声速飞机气动布局技术研究[J]. 航空科学技术, 2020, 31(11): 7-13. Li X K, Wang X, Liu J, et al. Research on the aerodynamic layout design for the horizontal take-off and landing hypersonic aircraft[J]. Aeronautical Science & Technology, 2020, 31(11): 7-13(in Chinese).
[3]	黄志澄. 高超声速飞行器空气动力学[M]. 北京: 国防工业出版社, 1995.
[4]	Lobbia M, Suzuki K. Multidisciplinary design optimization of hypersonic transport configurations using waveriders[R]. AIAA 2014-2359, 2014.
[5]	Rodi P E. Geometrical relationships for osculating cones and osculating flowfield waveriders[R]. AIAA 2011-1188, 2011.
[6]	Steelant J, Varvill R, Walton C, et al. Achievements obtained for sustained hypersonic flight within the LAPCAT-Ⅱ project[R]. AIAA 2015-3677, 2015.
[7]	Lee C. Lockheed Martin unveils SR-72[J]. Jane's Defence Weekly, 2013, 50(46): 6.
[8]	Guy N. Boeing unveils hypersonic 'Son-of-Blackbird' contender[EB/OL]. [2018-01-11]. http://awin.aviationweek.com/ArticlesStory.aspx?id=6267237e-e466-4c27-be75-cd963a5a6712.
[9]	Liu Z, Liu J, Ding F, et al. Novel methodology for wide-ranged multistage morphing waverider based on conical theory[J]. Acta Astronautica, 2017, 140: 362-369. doi: 10.1016/j.actaastro.2017.09.006
[10]	Li S B, Huang W, Wang Z G, et al. Design and aerodynamic investigation of a parallel vehicle on a wide-speed range[J]. Science China-Information Sciences, 2014, 57(12): 1-10.
[11]	Zhang T T, Wang Z G, Huang W, et al. A design approach of wide-speed-range vehicles based on the cone-derived theory[J]. Aerospace Science and Technology, 2017, 71: 42-51. doi: 10.1016/j.ast.2017.09.010
[12]	易怀喜, 王逗, 李珺, 等. 涡升力乘波体发展研究综述[J]. 航空工程进展, 2021, 12(6): 1-12. https://www.cnki.com.cn/Article/CJFDTOTAL-HKGC202106001.htm Yi H X, Wang D, Li J, et al. Overview on the develop-ment research of vortex lift waverider[J]. Advances in Aeronautical Science and Engineering, 2021, 12(6): 1-12(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKGC202106001.htm
[13]	Wang J F, Liu C Z, Bai P, et al. Design methodology of the waverider with a controllable planar shape[J]. Acta Astronautica, 2018, 151: 504-510. doi: 10.1016/j.actaastro.2018.06.048
[14]	Liu C Z, Liu R J, Meng X F, et al. Experimental investigation on off-design performances of double-swept waverider[J]. AIAA Journal, 2023, 61(4): 1596-1607. doi: 10.2514/1.J062254
[15]	陈冰雁, 刘传振, 纪楚群. 基于激波装配法的乘波体设计与分析[J]. 空气动力学学报, 2017, 35(3): 421-428. Chen B Y, Liu C Z, Ji C Q. Waverider design and analysis based on shock-fitting method[J]. Acta Aerodynamica Sinica, 2017, 35(3): 421-428(in Chinese).
[16]	李珺, 易怀喜, 王逗, 等. 基于投影法的双后掠乘波体气动性能[J]. 航空学报, 2021, 42(12): 124703. Li J, Yi H X, Wang D, et al. Research on aerodynamic performance of double swept waverider based on projection method[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 124703(in Chinese).
[17]	崔凯, 李广利, 胡守超, 等. 高速飞行器高压捕获翼气动布局概念研究[J]. 中国科学: 物理学力学天文学, 2013, 43(5): 652-661. https://www.cnki.com.cn/Article/CJFDTOTAL-JGXK201305007.htm Cui K, Li G L, Hu S C, et al. Conceptual studies of the high pressure zone capture wing configuration for high speed air vehicles[J]. Scientia Sinica-Physica, Mechan-ica & Astronomica, 2013, 43(5): 652-661(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-JGXK201305007.htm
[18]	Cui K, Li G L, Xiao Y, et al. High-pressure capturing wing configurations[J]. AIAA Journal, 2017, 55(6): 1909-1919.
[19]	李广利, 崔凯, 肖尧, 等. 高压捕获翼位置设计方法研究[J]. 力学学报, 2016, 48(3): 576-584. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201603006.htm Li G L, Cui K, Xiao Y, et al. The design method research for the position of high pressure capturing wing[J]. Chinese Journal of Theoretical and Applied Mecha-nics, 2016, 48(3): 576-584(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201603006.htm
[20]	李广利, 崔凯, 肖尧, 等. 高压捕获翼前缘型线优化和分析[J]. 力学学报, 2016, 48(4): 877-885. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201604014.htm Li G L, Cui K, Xiao Y, et al. Leading edge optimization and parameter analysis of high pressure capturing wings[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(4): 877-885(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201604014.htm
[21]	Li G L, Cui K, Xiao Y, et al. Effects of shock impingement on aerothermal and aerodynamic performance for high-pressure capturing wings[R]. AIAA 2017-2199, 2017.
[22]	王浩祥, 李广利, 杨靖, 等. 高压捕获翼构型亚跨超流动特性数值研究[J]. 力学学报, 2021, 53(11): 3056-3070. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB202111016.htm Wang H X, Li G L, Yang J, et al. Numerical study on flow characteristics of high-pressure capturing wing configuration at subsonic, transonic and supersonic regime[J]. Chinese Journal of Theoretical and Applied Mechanics, 2021, 53(11): 3056-3070(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB202111016.htm

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高压捕获翼双翼构型宽速域气动性能研究

doi: 10.19527/j.cnki.2096-1642.1049

作者简介:
肖尧(1988-)男, 博士, 工程师, 主要研究方向为宽域高超飞行器气动布局设计与优化。E-mail: xiaoyao@imech.ac.cn

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Research on Aerodynamic Performance of High-Pressure Capturing Wing with Bi-Wing Configuration in Wide-Speed Range

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高压捕获翼双翼构型宽速域气动性能研究

doi: 10.19527/j.cnki.2096-1642.1049

作者简介: 肖尧(1988-)男, 博士, 工程师, 主要研究方向为宽域高超飞行器气动布局设计与优化。E-mail: xiaoyao@imech.ac.cn

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Research on Aerodynamic Performance of High-Pressure Capturing Wing with Bi-Wing Configuration in Wide-Speed Range

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作者简介:
肖尧(1988-)男, 博士, 工程师, 主要研究方向为宽域高超飞行器气动布局设计与优化。E-mail: xiaoyao@imech.ac.cn