轴对称内锥流动中马赫盘的形成与演化

姬隽泽; 李祝飞; 司东现; 张涛; 施崇广; 尤延铖; 杨基明

doi:10.7638/kqdlxxb-2021.0360

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轴对称内锥流动中马赫盘的形成与演化

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 轴对称内锥流动中马赫盘的形成与演化
- Formation and evolution of Mach disk in axisymmetric internal conical flow
- 空气动力学学报 2022年40卷第1期页码：129-140
- 作者机构：
  
  1. 中国科学技术大学,合肥,230027
  2. 厦门大学,厦门,361102
- 作者简介：
  
  姬隽泽（1994-），男，河南平顶山人，博士研究生，研究方向：激波动力学. E-mail：jijunze@mail.ustc.edu.cn
  李祝飞*（1986-），男，博士，副教授，研究方向：高超声速空气动力学. E-mail：lizhufei@ustc.edu.cn
- 基金信息：
  
  国家自然科学基金面上项目（11872356，11772325，11621202）;国家自然科学基金联合基金项目（U21B6003）
- DOI：10.7638/kqdlxxb-2021.0360
  中图分类号： O354.5;V211.48
- 纸质出版：2022
- 稿件说明：
移动端阅览
姬隽泽, 李祝飞, 司东现, 等. 轴对称内锥流动中马赫盘的形成与演化[J]. 空气动力学学报, 2022, 40(1): 129−140.

JI Junze, LI Zhufei, SI Dongxian, et al. Formation and evolution of Mach disk in axisymmetric internal conical flow[J]. 2022, 40(1): 129-140.
姬隽泽, 李祝飞, 司东现, 等. 轴对称内锥流动中马赫盘的形成与演化[J]. 空气动力学学报, 2022, 40(1): 129−140. DOI： 10.7638/kqdlxxb-2021.0360

JI Junze, LI Zhufei, SI Dongxian, et al. Formation and evolution of Mach disk in axisymmetric internal conical flow[J]. 2022, 40(1): 129-140. DOI： 10.7638/kqdlxxb-2021.0360.

摘要

针对轴对称内收缩直锥流场中的马赫反射问题，采用无黏数值模拟结合理论分析，在来流马赫数6及直锥入口半径

恒定的条件下，以模型壁面前缘角度

和壁面长度

为几何参数，研究了内锥形激波汇聚增强过程以及马赫盘下游流动对马赫盘位置的影响。结果表明，壁面前缘角度

通过改变轴对称内锥形入射激波汇聚增强过程中达到von Neumann强度的位置，限定了马赫盘可能存在的位置范围；马赫盘位置还受其下游流动的影响，在不同的

和

条件下，马赫盘下游流管内声速喉道的形成机制可以划分为依赖或不依赖壁面尾缘膨胀波两种类型；对于不依赖于壁面尾缘膨胀波的情况，声速喉道形成之前流管内的压力仅与反射激波的波后非均匀压力相匹配，马赫盘的位置不随

而变化；对于依赖于壁面尾缘膨胀波的情况，声速喉道形成之前流管还需要匹配壁面尾缘膨胀波引起的压力变化；根据反射激波下游与马赫盘下游流管的压力匹配关系，可以求解马赫盘位置。

Abstract

The Mach reflection in axisymmetric flows

which is compressed by an internal cone

is investigated by using a combination of numerical simulations and theoretical analyses at a free-stream Mach number of 6. The effects of the leading-edge angle and cone length on the convergence behaviour of incident shocks and the flow downstream of Mach disk are examined. The results show that the leading-edge angle determines the point of von Neumann strength of the convergent incident shock

and also the location of the Mach disk. In addition to the shock convergence

the position of Mach disk is influenced by the downstream flow as well. According to whether the sonic throat of the stream tube downstream of the Mach disk is affected by the expansion waves generated from the trailing edge of the wall or not

two types of flow patterns downstream of the Mach disk can be classified depending on the leading-edge angle and the cone length. When the sonic throat is independent of the expansion waves

the pressure upstream of the sonic throat is balanced by the post-shock pressure of the reflected shock

and the position of Mach disk will not shift even if the cone length changes. On the other hand

when the sonic throat depends on the expansion waves

the stream tube upstream of the sonic throat needs to match the change of the pressure resulting from expansion waves. The position of Mach disk can be theoretically predicted based on the matching relations between the flow downstream of reflected shocks and the flow downstream of Mach disk.

关键词

Keywords

references

GOLDFELD M A, NESTOULIA R V. Numerical and experimental studies of 3D hypersonic inlet[C]//41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2003. AIAA 2003-14. doi: 10.2514/6.2003-14

QIAO W Y, YU A Y. Overview on integrated design of inward-turning inlet with aircraft forebody[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 43-59. (in Chinese)

ZUO F Y, MÖLDER S. Hypersonic wavecatcher intakes and variable-geometry turbine based combined cycle engines[J]. Progress in Aerospace Sciences, 2019, 106: 108-144. DOI:10.1016/j.paerosci.2019.03.001

YOU Y C. An overview of the advantages and concerns of hypersonic inward turning inlets[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, San Francisco, California. Reston, Virigina: AIAA, 2011. AIAA 2011-2269. doi: 10.2514/6.2011-2269

JI J Z, LI Z F, ZHANG E L, et al. Shock interactions in near-axisymmetric internal contraction flows[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 2-10. (in Chinese)

JI J Z, ZHANG E L, SI D X, et al. Non-uniform intensification behaviors of a converging conical shock wave[J]. Physics of Gases, 2021, 6(3): 1-14. (in Chinese)

ZHANG E L, LI Z F, JI J Z, et al. Converging near-elliptic shock waves[J]. Journal of Fluid Mechanics, 2021, 909: A2. DOI:10.1017/jfm.2020.910

JI J Z, LI Z F, ZHANG E L, et al. Intensification of non-uniformity in convergent near-conical hypersonic flow[J]. Journal of Fluid Mechanics, 2022, 931: A8. DOI:10.1017/jfm.2021.943

YANG Y, JIANG Z L, HU Z M. Advances in shock wave reflection phenomena[J]. Advances in Mechanics, 2012, 42(2): 141-161. (in Chinese)

FAN X Q, TAO Y, LI T J, et al. Advances in 2D shock reflection hysteresis phenomenon in steady supersonic flow fields[J]. Journal of Propulsion Technology, 2016, 37(8): 1411-1421. (in Chinese)

BEN-DOR G. Shock wave reflection phenomena[M]. New York, NY: Springer New York, 1992. doi: 10.1007/978-1-4757-4279-4

YOU Y C, LIANG D W. Investigation of internal compression flowfield for internal waverider-derived inlet[J]. Acta Aerodynamica Sinica, 2008, 26(2): 203-207. (in Chinese)

MÖLDER S. Internal, axisymmetric, conical flow[J]. AIAA Journal, 1967, 5(7): 1252-1255. DOI:10.2514/3.4179

SHOESMITH B, MÖLDER S, OGAWA H, et al. Shock reflection in axisymmetric internal flows[M]//Shock Wave Interactions. Cham: Springer International Publishing, 2018: 355-366. doi: 10.1007/978-3-319-73180-3_27

RYLOV A I. On the impossibility of regular reflection of a steady-state shock wave from the axis of symmetry[J]. Journal of Applied Mathematics and Mechanics, 1990, 54(2): 201-203. DOI:10.1016/0021-8928(90)90034-8

ISAKOVA N P, KRAIKO A N, P’YANKOV K S, et al. The amplification of weak shock waves in axisymmetric supersonic flow and their reflection from an axis of symmetry[J]. Journal of Applied Mathematics and Mechanics, 2012, 76(4): 451-465. DOI:10.1016/j.jappmathmech.2012.09.013

XU J, LUO J L, DAI W Y, et al. Effects of design parameters on hypersonic inward turning inlet and forebody[J]. Acta Aerodynamica Sinica, 2014, 32(5): 646-653. (in Chinese)

TANG P P, SU W Y, ZHANG K Y. Inverse design of axisymmetric basic flow field with destined flow distributions on wall of inner cone and center body[J]. Journal of Propulsion Technology, 2017, 38(8): 1709-1716. (in Chinese)

TAN L H. On the shape of shock waves in steady planar and axisymmetical Mach reflections[D]. Beijing: Tsinghua University, 2007. (in Chinese)

REN Y X, TAN L H, WU Z N. The shape of incident shock wave in steady axisymmetric conical Mach reflection[J]. Advances in Aerodynamics, 2020, 2(1): 474-484. DOI:10.1186/s42774-020-00047-6

MÖLDER S. Curved shock theory[J]. Shock Waves, 2016, 26(4): 337-353. DOI:10.1007/s00193-015-0589-9

SHI C G, HAN W Q, DEITERDING R, et al. Second-order curved shock theory[J]. Journal of Fluid Mechanics, 2020, 891: A21. DOI:10.1017/jfm.2020.158

MÖLDER S. Reflection of curved shock waves[J]. Shock Waves, 2017, 27(5): 699-720. DOI:10.1007/s00193-017-0710-3

FILIPPI A A, SKEWS B W. Streamlines behind curved shock waves in axisymmetric flow fields[J]. Shock Waves, 2018, 28(4): 785-793. DOI:10.1007/s00193-017-0783-z

SHI C G, ZHU C X, YOU Y C, et al. Method of curved-shock characteristics with application to inverse design of supersonic flowfields[J]. Journal of Fluid Mechanics, 2021, 920: A36. DOI:10.1017/jfm.2021.454

LI H, BEN-DOR G. A parametric study of Mach reflection in steady flows[J]. Journal of Fluid Mechanics, 1997, 341: 101-125. DOI:10.1017/s0022112097005375

GOUNKO Y P. Patterns of steady axisymmetric supersonic compression flows with a Mach disk[J]. Shock Waves, 2017, 27(3): 495-506. DOI:10.1007/s00193-016-0700-x

YOU Y C, ZHU C X, GUO J L. Dual waverider concept for the integration of hypersonic inward-turning inlet and airframe forebody[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany. Reston, Virginia: AIAA, 2009. AIAA 2009-7421. doi: 10.2514/6.2009-7421

LORRAIN P, BOYCE R. Supersonic fin-body interactions in an internal scramjet flow[J]. Journal of Propulsion and Power, 2011, 27(2): 319-329. DOI:10.2514/1.49226

ZHANG S K, LI J, QIN F, et al. Numerical investigation of combustion field of hypervelocity scramjet engine[J]. Acta Astronautica, 2016, 129: 357-366. DOI:10.1016/j.actaastro.2016.09.028

CHENG J B. Harten-Lax-van Leer-contact (HLLC) approximation Riemann solver with elastic waves for one-dimensional elastic-plastic problems[J]. Applied Mathematics and Mechanics, 2016, 37(11): 1517-1538. DOI:10.1007/s10483-016-2104-9

MLDER S. Curved aerodynamic shock waves[D]. Montreal: McGill University, 2012.

DORMAND J R, PRINCE P J. A family of embedded Runge-Kutta formulae[J]. Journal of Computational and Applied Mathematics, 1980, 6(1): 19-26. DOI:10.1016/0771-050X(80)90013-3

AZEVEDO D J. Analytical prediction of shock patterns in a high-speed, wedge bounded duct[D]. New York: State University of Nwe York, 1989.

GAO B. Wave structure and transition of Mach reflection in two-dimensional steady supersonic flows[D]. Beijing: Tsinghua University, 2010. (in Chinese)

MOUTON C A, HORNUNG H G. Mach stem height and growth rate predictions[J]. AIAA Journal, 2007, 45(8): 1977-1987. DOI:10.2514/1.27460

ZHANG T, SHI C G, ZHU C X, et al. On planar curved shock reflection[J]. Journal of Fluid Mechanics (submitted).

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