双射流激波针在高超声速下的减阻降热特性

王俊峰; 李珺; 罗世彬

doi:10.7638/kqdlxxb-2023.0040

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双射流激波针在高超声速下的减阻降热特性

研究论文 | 更新时间：2026-05-28

- 双射流激波针在高超声速下的减阻降热特性
- Drag and heat reduction performance of a dual-jet spike configuration in hypersonic flow
- 空气动力学学报 2024年42卷第2期页码：34-46
- 作者机构：
  
  中南大学航空航天技术研究院,长沙,410083
- 作者简介：
  
  王俊峰（1996—），男，湖南衡阳人，硕士研究生，研究方向：飞行器设计. E-mail：csutrip@163.com
  罗世彬*，教授，研究方向：空天飞行器设计. E-mail：luoshibin@csu.edu.cn
- 基金信息：
  
  国家自然科学基金（52202454）;湖南省重点研发计划项目(2021GK2011，2023GK2022)
- DOI：10.7638/kqdlxxb-2023.0040
  中图分类号： V211.3;V411.3;V435+.14
- 纸质出版：2024
- 稿件说明：
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王俊峰, 李珺, 罗世彬. 双射流激波针在高超声速下的减阻降热特性[J]. 空气动力学学报, 2024, 42(2): 34−46.

WANG Junfeng, LI Jun, LUO Shibin. Drag and heat reduction performance of a dual-jet spike configuration in hypersonic flow[J]. 2024, 42(2): 34-46.
王俊峰, 李珺, 罗世彬. 双射流激波针在高超声速下的减阻降热特性[J]. 空气动力学学报, 2024, 42(2): 34−46. DOI： 10.7638/kqdlxxb-2023.0040

WANG Junfeng, LI Jun, LUO Shibin. Drag and heat reduction performance of a dual-jet spike configuration in hypersonic flow[J]. 2024, 42(2): 34-46. DOI： 10.7638/kqdlxxb-2023.0040.

摘要

严酷的气动力和气动热环境是制约高超声速飞行器发展的两个重要因素，如何高效地降低高超声速飞行过程中的阻力和热流一直是设计者们追求的目标。为此，本文提出了一种结合后向射流和根部逆向射流的双射流激波针新构型。数值模拟研究发现：该构型能够利用后向射流产生的反作用力削减逆向射流附加阻力对减阻效果的影响，因此与无射流和单一射流方案相比，双射流激波针的流场结构显著改变，减阻降热效果极大提高。此外，增大激波针的长径比（

）有利于提高双射流激波针的减阻效果，但会使降热性能有所下降：在本文研究中，当激波针长径比从1增大到 4时，结构的总阻力系数降低了71.9%，而钝体总热流增大了13.7倍。同时，增大射流总压比

可以显著降低壁面热流：当逆向射流总压比（

）或后向射流总压比（

）大于0.4时，钝体壁面的热流极低并开始出现负值；然而，阻力系数随

和

的变化趋势恰好相反，随着

从0.2增大到0.5，由于逆向射流附加阻力的影响，结构总阻力系数增大了66.7%，而得益于后向射流的推力作用，结构总阻力系数则降低了59.3%。

Abstract

High aerodynamic drag and severe aeroheating are the two most important factors impeding the development of hypersonic vehicles. Thus

how to reduce the drag and heat flux effectively in hypersonic flight has attracted worldwide attention. In this paper

a novel strategy combining a spike and a dual-jet has been propose

d for the drag reduction and thermal protection. In this configuration

the reaction force generated by the root jet can balance the additional resistance of the rear jet

and the surface heat flux of the vehicle can also be reduced effectively. The flow characteristics and the drag/heat reduction efficiency is explored by numerical simulations. Meanwhile

the influence of the spike length and the total jet pressure on the drag and heat flux are quantitatively analyzed. The results reveal that flow structures of the dual-jet spike configuration are significantly changed

and the drag and heat reduction efficient is greatly improved compared to the cases with a single jet or without any jet. In addition

increasing the spike length ratio (

) is beneficial to improve the drag reduction performance

but has a negative effect on the thermal protection. Specifically

by increasing the spike length

from

= 1 to

= 4

the drag coefficient of the dual-jet spike configuration is decreased by 71.9%

while the total heat flux on the blunt body is increased by 13.7 times. On the other hand

the wall heat flux can be remarkably reduced by increasing the total jet pressure

and it becomes negative when the total pressure ratio of the opposing jet (

) or that of the rear jet (

) is larger than 0.4. However

the variation tendency of the drag coefficient with the increasing of

and

is completely opposite. Due to the drag induced by the opposing jet

the total drag coefficient of the dual-jet spike configuration is increased by 66.7% from

= 0.2 to

= 0.5. On the contrary

thanks to the thrust generated by the rear jet

the total drag coefficient of the dual-jet spike configuration is decreased by 59.3% from

= 0.2 to

= 0.5.

关键词

Keywords

references

ZHAO H Y, LIU S L, WU J, et al. Technical progress of hypersonic near-space vehicles abroad[J]. Aerodynamic Missile Journal, 2013(9): 8−13 (in Chinese). doi: 10.16338/j.issn.1009-1319.2013.09.015

GUO Y Q. Multi-discipline optimization for hypersonic vehicle shape design coupling aerodynamic and thermodynamic[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013 (in Chinese).

谢佐慰. 三叉戟 I 型导弹的头部[J]. 国外导弹技术, 1980(6): 1−15.

HUANG W, LI L Q, YAN L, et al. Drag and heat flux reduction mechanism of blunted cone with aerodisks[J]. Acta Astronautica, 2017, 138: 168−175. doi: 10.1016/j.actaastro.2017.05.040

KHARATI-KOOPAEE M, GAZOR H. Assessment of the aerodisk size on drag reduction and thermal protection of high-bluntness vehicles at hypersonic speeds[J]. Journal of Aerospace Engineering, 2017, 30(4): 04017008. doi: 10.1061/(asce)as.1943-5525.0000707

HUANG J, YAO W X. Multi-objective design optimization of blunt body with spike and aerodisk in hypersonic flow[J]. Aerospace Science and Technology, 2019, 93: 105122. doi: 10.1016/j.ast.2019.04.030

FAN B, HUANG J. Coupled fluid-thermal investigation on drag and heat reduction of a hypersonic spiked blunt body with an aerodisk[J]. Aerospace, 2022, 9(1): 19. doi: 10.3390/aerospace9010019

FAN B, HUANG J, SHAN X Y. Study on the hypersonic drag reduction mechanism of spike[J]. Machine Design and Manufacturing Engineering, 2021, 50(2): 75−78 (in Chinese). doi: 10.3969/j.issn.2095-509X.2021.02.016

SEBASTIAN J J, SURYAN A, DONG KIM H. Numerical analysis of hypersonic flow past blunt bodies with aerospikes[J]. Journal of Spacecraft and Rockets, 2016, 53(4): 669−677. doi: 10.2514/1.a33414

SRULIJES J, GNEMMI P, RUNNE K, et al. High-pressure shock tunnel experiments and CFD calculations on spike-tipped blunt bodies[C]// 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, St. Louis, Missouri. Reston, Virginia: AIAA, 2002. doi: 10.2514/6.2002-2918

HE K, YUAN H C. Drag and heat reduction characteristics and flow mechanism of typical aero-spikes[J]. Journal of Aerospace Power, 2022, 37(5): 1064−1078 (in Chinese). doi: 10.13224/j.cnki.jasp.20210178

DONG H, ZHANG X D, LIU S C, et al. Numerical and experimental study on opposing jet in hypersonic flow[J]. Acta Aerodynamica Sinica, 2022, 40(4): 101−109 (in Chinese). doi: 10.7638/kqdlxxb-2021.0240

HUANG W, LIU J, XIA Z X. Drag reduction mechanism induced by a combinational opposing jet and spike concept in supersonic flows[J]. Acta Astronautica, 2015, 115: 24−31. doi: 10.1016/j.actaastro.2015.04.025

QU F, SUN D, BAI J Q, et al. Numerical investigation of blunt body's heating load reduction with combination of spike and opposing jet[J]. International Journal of Heat and Mass Transfer, 2018, 127: 7−15. doi: 10.1016/j.ijheatmasstransfer.2018.06.154

ZHANG J, PENG C, CAI C F, et al. Optimization research on combination of spike and forward-facing jet using response surface methodology[J]. Acta Aerodynamica Sinica, 2015, 33(2): 204−210 (in Chinese). doi: 10.7638/kqdlxxb-2013.0101

GERDROODBARY M B. Numerical analysis on cooling performance of counterflowing jet over aerodisked blunt body[J]. Shock Waves, 2014, 24: 537−543. doi: 10.1007/s00193-014-0517-4

HUANG J, YAO W X, SHAN X Y. Numerical investigation on drag and heat reduction mechanism of combined spike and rear opposing jet configuration[J]. Acta Astronautica, 2019, 155: 179−190. doi: 10.1016/j.actaastro.2018.11.039

HUANG J, YAO W X. Parameter study on drag and heat reduction of a novel combinational spiked blunt body and rear opposing jet concept in hypersonic flows[J]. International Journal of Heat and Mass Transfer, 2020, 150: 119236. doi: 10.1016/j.ijheatmasstransfer.2019.119236

MA K, LI Y K, ZHU L, et al. Spike root oblique jet effect on drag and heat load reduction performance for hypersonic vehicles[J]. Acta Astronautica, 2020, 177: 588−603. doi: 10.1016/j.actaastro.2020.08.023

HE T Q, LUO S B. Research on drag and heat flux reduction of combination of spike and forward-facing jet in off-design regimes[J]. Flight Dynamics, 2019, 37(6): 46−50 (in Chinese). doi: 10.13645/j.cnki.f.d.20190805.003

GENG Y F, YU J, KONG W X. Investigation on a new method of adaptive drag reduction and non-ablation thermal protection system for hypersonic vehicles[J]. Acta Aerodynamica Sinica, 2012, 30(4): 492−501, 545.

JIANG Z L, LIU Y F, HAN G L, et al. Experimental demonstration of a new concept of drag reduction and thermal protection for hypersonic vehicles[J]. Acta Mechanica Sinica, 2009, 25(3): 417−419. doi: 10.1007/s10409-009-0252-8

ZHU L, CHEN X, ZHOU C S, et al. Research on effects of lateral jet on drag and heat reduction characteristics of spike in supersonic flows[J]. Journal of Propulsion Technology, 2018, 39(2): 326−334 (in Chinese). doi: 10.13675/j.cnki.tjjs.2018.02.010

ZHU L, LI Y K, GONG L K, et al. Coupled investigation on drag reduction and thermal protection mechanism induced by a novel combinational spike and multi-jet strategy in hypersonic flows[J]. International Journal of Heat and Mass Transfer, 2019, 131: 944−964. doi: 10.1016/j.ijheatmasstransfer.2018.11.119

ZHU L, CHEN X, TIAN X T, et al. Assessment on jet direction effect on drag and heat reduction efficiency for hypersonic vehicles[J]. Aerospace Science and Technology, 2020, 106: 105932. doi: 10.1016/j.ast.2020.105932

LI J, WANG J F, ZHAO Y T, et al. Research on combinational of configuration of spike and multi-jets in off-design regimes[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(9): 125949−125949 (in Chinese). doi: 10.7527/S1000-6893.2021.25949

HAYASHI K, ASO S, TANI Y. Experimental study on thermal protection system by opposing jet in supersonic flow[J]. Journal of Spacecraft and Rockets, 2006, 43(1): 233−236. doi: 10.2514/1.15332

ZHAO Y T, YAN C, WANG X Y, et al. Uncertainty and sensitivity analysis s of SST turbulence model on hypersonic flow heat transfer[J]. International Journal of Heat and Mass Transfer, 2019, 136: 808−820. doi: 10.1016/j.ijheatmasstransfer.2019.03.012

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