以CO2为工质的主动流动控制的降温减阻特性

doi:10.3901/JME.260545

机械工程学报 ›› 2026, Vol. 62 ›› Issue (14): 241-257.doi: 10.3901/JME.260545

• 可再生能源与工程热物理 • 上一篇下一篇

扫码分享

以CO₂为工质的主动流动控制的降温减阻特性

潘利生^1,2, 姚子康^1,2, 穆白³, 魏小林^1,2

1. 中国科学院力学研究所空天飞行高温气动全国重点实验室北京 100190;
2. 中国科学院大学工程科学学院北京 100049;
3. 北京建筑大学环境与能源工程学院北京 100044

收稿日期:2025-07-10 修回日期:2026-01-02 发布日期:2026-08-29
作者简介:潘利生(通信作者)，男，1982年出生，博士，研究员，硕士研究生导师。主要研究方向为飞行器热管理关键技术。E-mail：panlisheng@imech.ac.cn
基金资助:
国家自然科学基金资助项目(12372237)。

Heat Reduction and Drag Reduction Characteristics of Active Flow Control Using CO₂ as a Working Medium

PAN Lisheng^1,2, YAO Zikang^1,2, MU Bai³, WEI Xiaolin^1,2

1. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190;
2. School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049;
3. School of Environment and Energy Engineering, Beijing University of Civil Engineering and Architecture, Beijing 100044

Received:2025-07-10 Revised:2026-01-02 Published:2026-08-29

摘要/Abstract

摘要： 飞行器在大气层内高速飞行时，巨大的气动热流和气动阻力对飞行器结构材料和推力构成严峻挑战，以CO₂为工质的主动流动控制技术在降温减阻方面具有较大潜力。通过数值模拟方法，对飞行器头锥处CO₂逆向射流的降温减阻特性开展了研究。在不同射流参数下，CO₂射流前端可能出现凝华现象。当未出现凝华时，CO₂降温减阻能力和常规工质区别较小；当出现凝华时，降温性能大幅提升，但减阻能力有所减弱。随射流CO₂总温升高，凝华区固态CO₂占比减小，同时脱体激波距离增大。受凝华现象影响，减阻效果随CO₂射流总温的降低明显减弱；随射流总压增大，流场出现长射流与短射流的转变，钝体前压强呈现先减小后升高再减小的趋势，壁面St(斯坦顿数)则单调下降，降温效果不断提升；随着射流角度增大，射流的降温减阻效果不断减弱，当射流角度大于60°时，射流丧失了降温效果；随来流攻角增大，钝体迎风区和背风区的热环境和阻力环境不对称性增加，射流对迎风区的降温减阻效果减弱。

关键词: 主动流动控制, CO₂逆向射流, 降温减阻, 射流凝华, 飞行器热管理

Abstract: When flying at high speeds in the atmosphere，the tremendous aerodynamic heat flux and resistance pose significant challenges to both the structural materials and thrust of an aircraft. Active flow control technology，which employs CO₂ as the working fluid，holds great potential for cooling and drag reduction. The present study investigates the cooling and drag reduction characteristics of a CO₂ reverse jet at the nose cone of an aircraft using numerical simulations. Under different jet parameters，condensation may occur at the front end of the CO₂jet. When condensation does not occur，the cooling and drag reduction abilities of CO₂ are comparable to those of commonly fluids. However，when condensation takes place，the cooling effectiveness improves significantly while the drag reduction ability weakens. As the total temperature of CO₂ in the jet increases，the proportion of solid CO₂ in the condensation zone decreases，and the detachment shock distance increases. Due to the impact of the condensation phenomenon，the drag reduction effect significantly decreases with decreasing total temperature of the CO₂ jet. As the total pressure of the jet increases from low to high，the flow field undergoes a transition between long and short jets. The pressure in front of the blunt body initially decreases，then increases，and finally decreases again. The wall stanton number monotonically decreases，leading to an improved cooling effect. In contrast，increasing jet angle results in a weakened cooling and drag reduction effect. When the jet angle exceeds 60°，the cooling effect is lost entirely. Additionally，as the angle of attack of the incoming flow increases，the difference in thermal and resistance environments between the upwind and leeward regions of the blunt body becomes increasingly asymmetric，and the cooling and drag reduction effect of the jet on the upwind region is weakened.

Key words: active flow control, CO₂ opposing jet, cooling and drag reduction, jet condensation, aircraft thermal management

中图分类号:

V211
O351

潘利生, 姚子康, 穆白, 魏小林. 以CO₂为工质的主动流动控制的降温减阻特性[J]. 机械工程学报, 2026, 62(14): 241-257.

PAN Lisheng, YAO Zikang, MU Bai, WEI Xiaolin. Heat Reduction and Drag Reduction Characteristics of Active Flow Control Using CO₂ as a Working Medium[J]. Journal of Mechanical Engineering, 2026, 62(14): 241-257.

导出引用管理器 EndNote|Reference Manager|ProCite|BibTeX|RefWorks

链接本文: http://www.cjmenet.com.cn/CN/10.3901/JME.260545

http://www.cjmenet.com.cn/CN/Y2026/V62/I14/241

参考文献

[1] 李世斌. 逆向射流及其在高超声速飞行器中的减阻防热机理研究[D]. 长沙：国防科学技术大学，2019. LI Shibin. Mechanism investigation for drag and heat reduction of opposing jet on hypersonic vehicle[D]. Changsha：National University of Defense Technology，2019.
[2] 张一喆，李强，薛海，等. 基于路况识别的高速动车组构架损伤规律[J]. 机械工程学报，2018，54(8)：41-47. ZHANG Yizhe，LI Qiang，XUE Hai，et al. Damage law of high-speed EMU frame based on working condition recognition[J]. Journal of Mechanical Engineering，2018，54(8)：41-47.
[3] ROSE P H， STARK W L. Stagnation point heat-transfer measurements in dissociated air[J]. Journal of the Aerospace Sciences，1958，25：86-97.
[4] POLEZHAEV Y V. Will there or will there not be a hypersonic air plane[J]. Journal of Engineering Physics and Thermophysics，2000，73： 3-8.
[5] 丁锐. 发散冷却在高超声速飞行器上的应用可行性研究[D]. 合肥：中国科学技术大学，2020. DING Rui. Investigations on the application feasibility of transpiration cooling on hypersonic vehicles[D]. Hefei：University of Science and Technology of China，2020.
[6] YANG T，FOULKES T，KWON B. An integrated liquid metal thermal switch for active thermal management of electronics[J]. IEEE Transactions on Components，Packaging，and Manufacturing Technology，2019，9：2341-2351.
[7] LOVE E S. The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow[R]. Washington，D.C.：National Advisory Committee for Aeronautics，1952. NACA-RM-L52l19a.
[8] STALDER J R，INOUYE M. A method of reducing heat transfer to blunt bodies by air injection[R]. Washington，D.C.：NACA，1956.
[9] ROMEO D J，STERRETT J R. Exploratory investigation of the effect of a forward-facing jet on the bow shock of a blunt body in a Mach 6 free stream[R]. Washington，D.C.：NASA，1963：1-47.
[10] ROMEO D J，STERRETT J R. Flow field for sonic jet exhausting counter to hypersonic mainstream[J]. AIAA Journal，1965，3(3)：544-546.
[11] ADAMS R H，JARVINEN P O. The effects of retrorockets on the aerodynamic characteristics of conical aeroshell planetary entry vehicles[C]//8th Aerospace Sciences Meeting. New York：AIAA，1970： 70-219.
[12] SHEN Binxia，LIU Weiqiang. Thermal protection performance of a low pressure short penetration mode in opposing jet and its application[J]. International Journal of Heat and Mass Transfer，2020，163：120466.
[13] KIM Y，ROH T S，HUH H. Study on the combined effect of various injection conditions on the drag reduction by a counter–flow jet in supersonic flow[J]. Aerospace Science and Technology，2020，98：105580.
[14] BIBI A，MAQSOOD A，SHER S. Drag reduction of supersonic blunt bodies using opposing jet and nozzle geometric variations[J]. Aerospace Science and Technology，2017，69：244-256.
[15] HUANG Jie，YAO Weixing，JIANG Zhiping. Penetration mode effect on thermal protection system by opposing jet[J]. Acta Astronautica，2019，160：206-215.
[16] LI Shibin，WANG Zhenguo，HUANG Wei. Effect of the injector configuration for opposing jet on the drag and heat reduction[J]. Aerospace Science and Technology，2016，51：78-86.
[17] LI Shibin，WANG Zhenguo，HUANG Wei. Drag and heat reduction performance for an equal polygon opposing jet[J]. Journal of Aerospace Engineering，2017，30：04016065.
[18] SRIRAM R，JAGADEESH G. Film cooling at hypersonic Mach numbers using forward facing array of micro–jets[J]. International Journal of Heat and Mass Transfer，2009，52：3654-3664.
[19] WARREN F W G. An experimental investigation of the effect of ejecting a coolant gas at the nose of a blunt body[J]. Journal of Fluid Mechanics，1960，8：400-417.
[20] JIANG Zonglin，LIU Yunfeng，HAN Guilai. Experimental demonstration of a new concept of drag reduction and thermal protection for hypersonic vehicles[J]. Acta Mechanica Sinica，2009，25：417-419.
[21] 秦燕华，庄逢甘，沈礼敏. 展向射流控制机翼头锥涡的机理及其应用[J]. 空气动力学学报，1998，16：267-275. QIN Yanhua，ZHUANG Fenggan，SHEN Limin. An experimental study on controlling vortex over wing by using spanwise blowing[J]. Acta Aerodynamica Sinica，1998，16：267-275.
[22] HAYASHI K，ASO S. Effect of pressure ratio on aerodynamic heating reduction due to opposing jet[C]//33rd Fluid Dynamics Conference and Exhibit. Reston：AIAA，2003.

以CO₂为工质的主动流动控制的降温减阻特性

Heat Reduction and Drag Reduction Characteristics of Active Flow Control Using CO₂ as a Working Medium

PDF

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]	杨毅晟, 李明, 杨泽源, 闫喜强, 严思杰, 丁汉. 数字技术赋能风洞全生命周期体系[J]. 机械工程学报, 2026, 62(7): 97-113.
[2]	周德开, 潘傲, 刘军民, 李朋春, 邵天双, 崔立冬, 李隆球. 风洞活动带地板技术研究现状与展望[J]. 机械工程学报, 2025, 61(18): 313-329.
[3]	郭鹏, 冯和英, 王勇, 彭叶辉, 崔盼望, 余荣科. 梯度分布多孔尾缘对翼型低速扰流自噪声的影响[J]. 机械工程学报, 2025, 61(17): 150-160.
[4]	王维民, 刘延振, 林昱隆, 李天晴. 基于叶片振动的航空发动机喘振预警及识别方法[J]. 机械工程学报, 2024, 60(21): 122-131.
[5]	贾永兴, 景璟, 梅元贵. 单列高速列车通过隧道空气阻力数值模拟研究[J]. 机械工程学报, 2020, 56(4): 193-200.
[6]	黄祯君, 张涛, 王杰. 高焓高热流条件下半椭圆喷管冷却结构设计与分析[J]. 机械工程学报, 2019, 55(18): 157-164.
[7]	张振辉, 李栋. 合成射流激励器的特性及其后台阶流动控制应用[J]. 机械工程学报, 2018, 54(6): 224-232.
[8]	陈鹏飞, 吴锋, 徐全勇, 彭晋, 徐倩楠. 可变面积的非对称姿态模拟射流喷管设计与仿真[J]. 机械工程学报, 2018, 54(2): 184-190.
[9]	陈广强, 杨云军, 雷娟棉, 陈冰雁, 刘周. 锥台型气体润滑动压轴承动力学数值模拟研究[J]. 机械工程学报, 2016, 52(4): 185-191.
[10]	梅元贵, 张成玉, 周朝晖, 贾永兴, 吴明. 单列高速列车通过特长隧道时耳感不适问题研究[J]. 机械工程学报, 2015, 51(14): 100-107.
[11]	贾永兴;杨永刚;梅元贵. 基于一维流动模型的高速列车隧道压力波特性[J]. , 2014, 50(24): 106-114.
[12]	李文;朱阳历;陶海亮;谭春青;陈海生. 高空低Re数下低压涡轮气动特性[J]. , 2013, 49(4): 128-133.
[13]	肖军;谷传纲. 基于全隐式紧耦合算法的颤振数值分析[J]. , 2010, 46(22): 156-166.
[14]	金光远;欧阳华;杜朝辉. 叶片弯掠轴流风扇内瞬态流动的试验研究[J]. , 2013, 49(4): 154-162.
[15]	孙岩;张征宇;朱伟军;王超;李涤尘;赵星磊. 考虑弹性变形的光敏树脂风洞模型设计方法[J]. , 2011, 47(8): 169-174.