超声速侧向喷流干扰流场的稀薄效应研究

卢天琪; 孔小平; 刘艳; 陈浩

doi:10.7638/kqdlxxb-2023.0082

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

超声速侧向喷流干扰流场的稀薄效应研究

研究论文 | 更新时间：2026-07-27

- 超声速侧向喷流干扰流场的稀薄效应研究
- The rarefaction effects on the supersonic lateral jet/freestream interaction
- 空气动力学学报 2024年42卷第7期页码：14-26
- 作者机构：
  
  1. 扬州大学机械工程学院,扬州,225009
  2. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
  3. 航空工业沈阳飞机设计研究所,沈阳,110000
- 作者简介：
  
  卢天琪（1998—），男，江苏南通人，研究生，研究方向：高速空气动力学. E-mail：452429435@qq.com
  陈浩*（1989—），男，四川广安人，讲师，研究方向：稀薄气体动力学. E-mail：tjuchenhao@163.com
- 基金信息：
  
  国家自然科学基金（12102381）;基础加强1912项目
- DOI：10.7638/kqdlxxb-2023.0082
  中图分类号： V211.3
- 纸质出版：2024
- 稿件说明：
移动端阅览
卢天琪, 孔小平, 刘艳, 等. 超声速侧向喷流干扰流场的稀薄效应研究[J]. 空气动力学学报, 2024, 42(7): 14−26.

LU Tianqi, KONG Xiaoping, LIU Yan, et al. The rarefaction effects on the supersonic lateral jet/freestream interaction[J]. 2024, 42(7): 14-26.
卢天琪, 孔小平, 刘艳, 等. 超声速侧向喷流干扰流场的稀薄效应研究[J]. 空气动力学学报, 2024, 42(7): 14−26. DOI： 10.7638/kqdlxxb-2023.0082

LU Tianqi, KONG Xiaoping, LIU Yan, et al. The rarefaction effects on the supersonic lateral jet/freestream interaction[J]. 2024, 42(7): 14-26. DOI： 10.7638/kqdlxxb-2023.0082.

摘要

反作用控制系统（RCS）具有响应快速、控制灵活的特点，在临近空间飞行任务中可实现飞行器的精准姿轨控制，然而连续流区建立的侧向喷流干扰在稀薄流域逐渐弱化甚至失效。为了解决这一问题，针对平板和楔形块两种构型，采用直接模拟蒙特卡罗方法（DSMC）开展了超声速侧向喷流/高超声速来流相互干扰流场的稀薄效应研究。结果表明：平板和楔形块喷流干扰流场均出现经典干扰结构，如多涡、多激波等；特别地，楔形块构型中出现类似马赫杆的特殊弓形激波结构，其由大入射角前缘激波与喷流弓形激波相互干扰而形成。随着流动逐渐变得稀薄，喷口前涡结构逐渐减小至消失，激波增厚且干扰减弱，特殊弓形激波结构逐渐消失。基于壁面压力、切应力和热流系数分别定义了3种无量纲干扰强度和干扰区长度，均与克努森数呈近似幂律递减关系。超声速喷流干扰作用对平板与楔形块壁面热流的增长最显著，受到的稀薄效应抑制作用也最强；干扰区长度与气动特性参数无关，与本文的两种几何构型也无关。

Abstract

The reaction control system (RCS) relies on the interaction between the lateral jet and the freestream to achieve precise attitude control

quick response

and flexible flow field control in near space. However

these advantages in the continuum region will not be evident in rarefied flows. This paper utilizes direct simulation Monte Carlo (DSMC) to investigate the effects of rarefaction on the supersonic lateral jet/hypersonic freestream interaction over a flat plate and a wedge. Typical flow structures

such as vortical structures and shock waves

are observed in the continuous flow fields for both the flat-plate and wedge configurations. Additionally

a distinct bow shock similar to the Mach stem emerges in the flow field above the wedge

resulting from the interaction between the shock wave at the leading edge with a significant incident angle and the jet's bow shock wave. In rarefied flow fields

vortical structures downstream of the jet disappear

the shock wave thickens

and the distinct bow shock gradually diminishes. Three dimensionless interaction strength groups and the length of the interaction region

quantified by the wall pressure

shear stress

and heat flux

respectively

decrease exponentially with the global Knudsen number. Specifically

the interaction of the supersonic jet has the most significant impact on the increase in wall heat flux for both the flat-plate and wedge configurations.

关键词

Keywords

references

LI S X . Progress in aerodynamics of combination control for vehicles at high speed[J ] . Advances in Mechanics, 2009 , 39 ( 6 ): 740 − 755 (in Chinese).

SHANG J S, MCMASTER D L, SCAGGS N, et al . Interaction of jet in hypersonic cross stream[J ] . AIAA Journal, 1989 , 27 ( 3 ): 323 − 329 .

SPAID F W, ZUKOSKI E E . A study of the interaction of gaseous jets from transverse slots with supersonic external flows[J ] . AIAA Journal, 1968 , 6 ( 2 ): 205 − 212 .

HUANG W, LIU W D, LI S B, et al . Influences of the turbulence model a nd the slot width on the transverse slot injection flow field in supersonic flows[J ] . Acta Astronautica, 2012 , 73 : 1 − 9 .

ERDEM E, KONTIS K . Numerical and experimental investigation of transverse injection flows[J ] . Shock Waves, 2010 , 20 ( 2 ): 103 − 118 .

ASO S, OKUYAMA S, ANDO Y, et al. Two-dimensional and three-dimensional mixing flow fields in supersonic flow induced by injected secondary flows through traverse slot andcircular nozzle[C]// 31st Aerospace Sciences Meeting, Reno, NV, USA. Reston, Virigina: AIAA, 1993: 489.

KARAGOZIAN A R . Transverse jets and their control[J ] . Progress in Energy and Combustion Science, 2010 , 36 ( 5 ): 531 − 553 .

DICKMANN D, LU F. Jet in supersonic crossflow on a flat plate[C]//25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, San Francisco, California. Reston, Virigina: AIAA, 2006: 3451.

LI B, WANG X Z, LIU X M . Numerical investigation of multi-lateral jets interactions flow chara cteristics at high angle of attack[J ] . Acta Aeronautica et Astronautica Sinica, 2015 , 36 ( 9 ): 2828 − 2839 (in Chinese).

LIANG J, YAN C, YANG Y G, et al . Parallel DSMC simulation of lateral jet interaction in rarefied transitional region[J ] . Journal of Astronautics, 2011 , 32 ( 5 ): 1012 − 1018 (in Chinese).

WANG Z, JIANG C W, GAO Z X, et al . Prediction for the separation length of two-dimensional sonic injection with high-speed crossflow[J ] . AIAA Journal, 2017 , 55 ( 3 ): 832 − 847 .

KARPUZCU I T, LEVIN D A, MAMROL D, et al. Jet flow-shockwave interactions in a hypersonic flow using experimental and kinetic methods[C]//AIAA SCITECH 2022 Forum, San Diego, CA Virtual. Reston, Virginia: AIAA, 2022: 1577.

SHAO X Y. Research on aerodynamic characteristics of lateral jet in hypersonic flow by the DSMC method[D]. Shanghai: Shanghai Jiao Tong University, 2018(in Chinese).

BOWERSOX R D W, FAN H G, LEE D N . Sonic injection into a Mach 5.0 freestream through diamond orifices[J ] . Journal of Propulsion and Power, 2004 , 20 ( 2 ): 280 − 287 .

ZHANG Q B, LU X L, SHA S . Effects of the high temperature exhaust plume reaction on lateral jet interactions[J ] . Journal of Experiments in Fluid Mechanics, 2019 , 33 ( 6 ): 34 − 40 (in Chinese).

ROBERTS G T, SCHURICHT P H, MUDFORD N R . Heating enhancement caused by a transverse control jet in hypersonic flow[J ] . Shock Waves, 1998 , 8 ( 2 ): 105 − 112 .

GÜLHAN A, SCHÜTTE G, STAHL B . Experimental study on aerothermal heating caused by jet-hypersonic crossflow interaction[J ] . Journal of Spacecraft and Rockets, 2008 , 45 ( 5 ): 891 − 899 .

TAGUCHI M, MORI K, NAKAMURA Y . Experimental study on aerodynamic heating induced by dual injections into hypersonic cross flow[J ] . International Journal of Aerospace Engineering, 2017 , 2017 : 1 − 16 .

BAE J Y, KIM J, LEE N, et al . Measurement of surface heat transfer caused by interaction of sonic jet and supersonic crossflow near injection hole[J ] . Aerospace Science and Technology, 2021 , 119 : 107180 .

BIRD G A. Molecular gas dynamics and the direct simulation of gas flows[M]. Oxford, England, U. K: Oxford University Press, 1994: 9−16.

BOYD I D . Computation of hypersonic flows using the direct simulation Monte Carlo method[J ] . Journal of Spacecraft and Rockets, 2015 , 52 ( 1 ): 38 − 53 .

THAYER W J III, CORLETT R C . Gas dynamic and transport phenomena in the two-dimensional jet interaction flowfield[J ] . AIAA Journal, 1972 , 10 ( 4 ): 488 − 493 .

DING D M, CHEN H, SHAO X Y, et al. DSMC study of the real gas effect on lateral jet interaction of THAAD-like missile[C]//31st International Symposium on Rarefied Gas Dynamics, Glasgow, UK. Maryland, USA: AIP Publishing, 2019, 2132(1): 070018.

ZHAUNG H J, DING D M, CHEN H, et al . Effectiveness of reaction control system in hypersonic rarefied reactive flow[J ] . Journal of Spacecraft and Rockets, 2022 , 59 ( 3 ): 717 − 727 .

CHEN H, ZHANG B, LIU H . Non-rankine–hugoniot shock zone of Mach reflection in hypersonic rarefied flows[J ] . Journal of Spacecraft and Rockets, 2016 , 53 ( 4 ): 619 − 628 .

KULAKHMETOV M, ALEXEENKO A A . Modeling uncertainties in direct simulation Monte Carlo calculations of hypersonic leading-edge flow[J ] . Journal of Spacecraft and Rockets, 2012 , 49 ( 3 ): 461 − 473 .

卢天琪、陈浩、孔小平. 变攻角高超声速平板横向喷流中稀薄效应及气动特性研究[C]//第二十届全国激波与激波管学术会议, 合肥, 2022.

GAO B, WU Z N . A study of the flow structure for Mach reflection in steady supersonic flow[J ] . Journal of Fluid Mechanics, 2010 , 656 : 29 − 50 .

CHEN H, LIN Z, LIU C C, et al . Uncertai nty quantification of vacuum plume simulations using direct simulation Monte Carlo method[J ] . Journal of Propulsion Technology, 2020 , 41 ( 1 ): 73 − 84 (in Chinese).

CHEN H, ZHANG B, LIU H . Role of chemical reactions in the stagnation point heat flux of rarefied hypersonic cylinder flows[J ] . Physics of Fluids, 2020 , 32 ( 9 ): 096105 .

DING D M, CHEN H, MA Z, et al . Heat flux estimation of the cylinder in hypersonic rarefied flow based on neural network surrogate model[J ] . AIP Advances, 2022 , 12 ( 8 ): 085314 .

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

低温振动非平衡流动数值模拟研究

高压捕获翼构型的跨流域气动特性

基于动理学模型的多尺度随机粒子方法

气体稀薄效应对热流计算的影响

高速飞行器气动推进一体化性能参数化分析