真实气体效应下飞行/喷流参数对逆向喷流减阻降热特性的影响

杜佳宝; 吴锦水; 段润泽

doi:10.7638/kqdlxxb-2024.0143

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真实气体效应下飞行/喷流参数对逆向喷流减阻降热特性的影响

研究论文 | 更新时间：2026-05-28

- 真实气体效应下飞行/喷流参数对逆向喷流减阻降热特性的影响
- Influence of flight/jet parameters on drag and heat reduction characteristics of opposing jet under real gas effects
- 空气动力学学报 2026年44卷第1期页码：96-108
- 作者机构：
  
  1. 河北工业大学能源与环境工程学院,天津,300401
  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
- 作者简介：
  
  杜佳宝（2001—），男，山东临沂人，硕士研究生，研究方向：逆向喷流主动热防护技术. E-mail： dujiabao2002@163.com
  吴锦水*，高级工程师，研究方向：发汗冷却,气膜冷却. E-mail： wjscardc@126.com
- 基金信息：
  
  国家重点研发计划（JZX2023，KTZ2024）
- DOI：10.7638/kqdlxxb-2024.0143
  中图分类号： V211.3;V211.7
- 纸质出版：2026
- 稿件说明：
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杜佳宝, 吴锦水, 段润泽. 真实气体效应下飞行/喷流参数对逆向喷流减阻降热特性的影响[J]. 空气动力学学报, 2026, 44(1): 96−108.

Du Jiabao, Wu Jinshui, Duan Runze. Influence of flight/jet parameters on drag and heat reduction characteristics of opposing jet under real gas effects[J]. 2026, 44(1): 96-108.
杜佳宝, 吴锦水, 段润泽. 真实气体效应下飞行/喷流参数对逆向喷流减阻降热特性的影响[J]. 空气动力学学报, 2026, 44(1): 96−108. DOI： 10.7638/kqdlxxb-2024.0143

Du Jiabao, Wu Jinshui, Duan Runze. Influence of flight/jet parameters on drag and heat reduction characteristics of opposing jet under real gas effects[J]. 2026, 44(1): 96-108. DOI： 10.7638/kqdlxxb-2024.0143.

摘要

高速飞行器飞行时会产生大量的气动阻力和气动热，周围气体分子的振动能和电子能被激发，并发生离解和电离等化学反应，真实气体效应不可忽略。逆向喷流技术作为一种主动热防护技术，已受到广泛关注，因此有必要对真实气体效应下的逆向喷流减阻降热特性进行深入研究。本文基于数值计算方法，对比了不同气体模型下逆向喷流系统的性能，发现热化学非平衡气体模型对钝体阻力与热流的预测更为准确，更适用于高速飞行器的气动热环境分析。采用二维可压缩Navier-Stokes方程和热化学非平衡气体模型模拟了钝体在不同飞行条件下喷流系统的流场分布，研究了真实气体效应下飞行/喷流参数对喷流流场结构、钝体气动阻力和气动热的影响。结果表明：飞行马赫数增大，钝体的总阻力和总热流显著增加，飞行马赫数从8增大到12，钝体的总阻力系数提高了29.30%，总热流增大了8.53倍。飞行攻角为10°时，迎风面和背风面的壁面压力相差2.57倍，最大热流密度相差16.17倍。增大飞行高度会降低来流总压，使喷流穿透能力增强，飞行高度从32 km增加到36 km，钝体峰值压力降低了36.34 kPa，峰值热流密度降低了1.32 MW/m

。增大喷流压比对降低钝体总阻力和总热流具有显著效果，当喷流压比为0.014时，系统减阻降热效果最佳，总阻力系数和总热流相较无喷流时分别降低41.32%和73.55%。喷流温度变化主要影响近壁面温度分布，温度升高虽对钝体总阻力系数影响甚微，但会提高钝体总热流，导致系统减阻降热效率降低。

Abstract

Hypersonic vehicles experience significant aerodynamic drag and thermal loads during high-speed flight

where vibrational and electronic energy excitation of surrounding gas molecules

along with chemical reactions such as dissociation and ionization

make real gas effect non-negligible. As a novel active thermal protection method

opposing jet technology has attracted considerable research attention. Therefore

it is essential to conduct a detailed investigation of drag and heat reduction capabilities of opposing jet under real gas effects. Based on numerical simulation methods

this study compares the performance of opposing jet systems under different gas models

and finds that compared to other models

the non-equilibrium thermochemical gas model provides more accurate predictions of drag and heat flux on blunt bodies

making it more suitable for analyzing aerodynamic thermal environments in high-speed aircraft. Therefore

a two-dimensional compressible Navier-Stokes equations and a thermochemical non-equilibrium gas model are employed to simulate the flow field of the opposing jet system under various flight conditions. The effects of real gas effects and flight/jet parameters on the flow field structure

aerodynamic drag

and heat of a blunt body are investigated. Results indicate that an increase in flight Mach number significantly raises total temperature and pressure

with the total drag coefficient increasing by 29.30% and the total heat flux increasing by 8.53 times when the flight Mach number increases from 8 to 12. The presence of a flight angle of attack disrupts the symmetry of the flow field

with a wall pressure difference of 2.57 times and a heat flux difference of up to 16.17 times between the windward and leeward sides at an angle of attack of 10°. Increased flight altitude decreases the total pressure of free-flow

resulting in a reduced free-flow intensity and enhanced jet-flow penetration capability. As the flight altitude increases from 32 km to 36 km

the maximum pressure of the blunt body decreases by 36.34 kPa

and the maximum heat flux decreases by 1.32 MW/m². Increasing the jet pressure ratio significantly improves the total drag and heat flux. At a jet pressure ratio of 0.014

the system demonstrates optimal drag and heat flux reduction

with the total drag coefficient and heat flux reduced by 41.32% and 73.55%

respectively

compared to no-jet conditions. Changes in jet temperature have a significant impact on the near-wall temperature distribution. While increasing the jet temperature has little effect on total drag coefficient

it increases total heat flux

thereby reducing the overall drag and heat reduction efficiency of the system.

关键词

Keywords

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