高速来流下逆向射流长短穿透模态减阻防热机理

许浩楠; 李建飞; 李雪英; 任静

doi:10.7638/kqdlxxb-2024.0054

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高速来流下逆向射流长短穿透模态减阻防热机理

研究论文 | 更新时间：2026-05-28

- 高速来流下逆向射流长短穿透模态减阻防热机理
- Drag and heat reduction mechanism in long and short penetration modes of opposing jet under high-speed flow
- 空气动力学学报 2025年43卷第12期页码：64-80
- 作者机构：
  
  清华大学能源与动力工程系,北京,100084
- 作者简介：
  
  许浩楠（1998—），黑龙江哈尔滨人，博士研究生，研究方向：高速减阻降热方法. E-mail：xhn_9810@163.com
  李雪英*，副研究员，研究方向：空天动力主动热防护方法. E-mail：li_xy@tshinghua.edu.cn
- 基金信息：
  
  国家自然科学基金委面上项目（52476031）
- DOI：10.7638/kqdlxxb-2024.0054
  中图分类号： V211.3;V411.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
许浩楠, 李建飞, 李雪英, 等. 高速来流下逆向射流长短穿透模态减阻防热机理[J]. 空气动力学学报, 2025, 43(12): 64−80.

XU Haonan, LI Jianfei, LI Xueying, et al. Drag and heat reduction mechanism in long and short penetration modes of opposing jet under high-speed flow[J]. 2025, 43(12): 64-80.
许浩楠, 李建飞, 李雪英, 等. 高速来流下逆向射流长短穿透模态减阻防热机理[J]. 空气动力学学报, 2025, 43(12): 64−80. DOI： 10.7638/kqdlxxb-2024.0054

XU Haonan, LI Jianfei, LI Xueying, et al. Drag and heat reduction mechanism in long and short penetration modes of opposing jet under high-speed flow[J]. 2025, 43(12): 64-80. DOI： 10.7638/kqdlxxb-2024.0054.

摘要

逆向射流技术作为一种主动流动控制方法，有望同时实现高速飞行器的减阻和防热。为研究逆向射流在不同流动模态下的减阻防热机制，以二维钝头模型为研究对象，采用经验证的数值模拟方法在马赫数10来流情况下，通过改变射流滞止压比（

PsR

= 0～6.0）来开展研究。研究结果表明：随着射流滞止压比的增大，逆向射流将分别经历非稳态短穿透射流模态、非稳态长穿透射流模态和稳态短穿透射流模态。非稳态短穿透射流模态由于不能满足飞行器减阻防热需求在实际应用时应避免出现。非稳态长穿透射流模态虽能凭借较长的激波脱体距离减小交界面锥顶角，从而在低射流压比下获得优异的减阻效果，但其锐化的交界面结构会引发更强的主流气动加热，加之射流总焓较低，共同导致了防热效果的恶化。对于稳态短穿透射流模态，射流压比增大导致激波脱体距离增加，进而使交界面锥顶角减小，减阻效果提升；同时，交界面驻点位置气动热流密度的下降，以及射流总焓的提高提升了防热效果。综上所述，虽然长穿透射流模态与短穿透射流模态表现出不同的减阻与防热特性，但其内在的减阻防热物理机制是一致的，稳态短穿透射流模态更适合用于解决高速飞行强气动阻力与气动热问题。

Abstract

Opposing jet technique

as an active flow control method

has the potential for efficient drag and heat reduction in high-speed vehicles. To investigate the drag and heat reduction mechanism of the opposing jet in different typical flow modes

the surface pressure coefficient and adiabatic cooling efficiency are numerically calculated for a blunt body featuring an opposing jet orifice

under an incoming flow of

= 10

at different jet stagnation pressure ra

tios (

PsR

= 0～6.0). The results show that with the increase of

PsR

the opposing jet experiences three typical flow modes: unsteady short penetration mode

unsteady long penetration mode and steady short penetration mode. The unsteady short penetration mode fails to achieve effective heat and drag reduction and should be avoided. The unsteady long penetration mode achieves high drag reduction at low

PsR

values

attributable to the reduced interface cone apex angle brought by the longer bow shock stand-off distance

however

its heat reduction performance is compromised due to increased mainstream aero-heating from the sharpened interface structure and reduced opposing jet total enthalpy. In the steady short penetration mode

increasing

PsR

enhances drag reduction by decreasing the interface cone apex angle and increasing the bow shock stand-off distance

while heat reduction improves due to reduced mainstream aero-heating at the interface and increased opposing jet total enthalpy. Although the long penetration and short penetration mode show different drag and heat reduction characteristics

their intrinsic physical mechanisms of drag and heat reduction are consistent. The steady short penetration mode is more suitable for addressing the challenges of high aerodynamic drag and heating in hypersonic flight.

关键词

Keywords

references

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