Effects of gas ejection on aerodynamic force and heating of near-space lifting vehicles

LI Junhong; CHEN Zhi; JIN Xuhong; MIAO Wenbo

doi:10.7638/kqdlxxb-2024.0008

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Effects of gas ejection on aerodynamic force and heating of near-space lifting vehicles

更新时间：2026-07-27

- Effects of gas ejection on aerodynamic force and heating of near-space lifting vehicles
- Vol. 42, Issue 8, Pages: 1-9(2024)
- 作者机构：
  
  1. 中国航天空气动力技术研究院,北京,100074
  2. 中国航天科技集团有限公司航天飞行器气动热防护实验室,北京,100048
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0008
  CLC： V211.3;TP6
- Published：2024
- 稿件说明：
移动端阅览
李俊红, 陈智, 靳旭红, 等. 气体引射对临近空间升力体飞行器气动力热影响[J]. 空气动力学学报, 2024, 42(8): 1−9.

LI Junhong, CHEN Zhi, JIN Xuhong, et al. Effects of gas ejection on aerodynamic force and heating of near-space lifting vehicles[J]. 2024, 42(8): 1-9.
李俊红, 陈智, 靳旭红, 等. 气体引射对临近空间升力体飞行器气动力热影响[J]. 空气动力学学报, 2024, 42(8): 1−9. DOI： 10.7638/kqdlxxb-2024.0008

LI Junhong, CHEN Zhi, JIN Xuhong, et al. Effects of gas ejection on aerodynamic force and heating of near-space lifting vehicles[J]. 2024, 42(8): 1-9. DOI： 10.7638/kqdlxxb-2024.0008.

摘要

针对临近空间高速飞行器的降热减阻需求，采用三维数值模拟手段研究了临近空间典型升力体飞行器气动力/热特性，分析了壁面气体质量引射对气动力/热特性的影响规律和作用机理。结果表明：壁面质量引射会略微增大激波脱体距离，对激波层和速度边界层有增厚作用，降低了边界层内的速度梯度，使得表面剪切力减小，从而具有较好的减阻效果。对于典型的升力体构型，在高度为60～70 km时，壁面质量引射减阻效率均不低于47.5%；在高度为80 km时，壁面质量引射减阻效率不低于10.2%；且壁面质量引射减阻效果随攻角增大而增强，随飞行高度升高而减弱。同时，壁面引射排出的低温气体对飞行器具有隔热保护作用，因此壁面质量引射能显著降低迎风面的热流，具有较好的降热效果。

Abstract

In order to meet the thermal and drag reduction requirements of high speed vehicles in near space

three-dimensional numerical simulation method was used to study the typical lift-body vehicle in near space. The aerodynamic thermal characteristics of the vehicle were analyzed

and the law and mechanism of mass ejection on the aerodynamic thermal characteristics were analyzed. The results demonstrate that wall mass ejection can slightly increase the detachment distance of the shock wave

thicken the shock wave layer and velocity boundary layer

and reduce the velocity gradient within the boundary layer

resulting in satisfactory drag reduction performance. For a typical lifting body configuration

wall mass ejection can reduce skin friction by more than 47.5% at flight altitudes ranging from 60 km to 70 km

while 10.2% at 80 km altitude. The drag reduction effect of wall mass ejection is enhanced with the increase of the attack angle

while weaken with the increment of flight altitude. Wall mass ejection not only thickens the temperature boundary layer but also provides thermal protection by ejecting low-temperature gas

which can significantly reduce the skin heat flux on the windward side.

关键词

Keywords

references

SHEN B X, ZENG L, LIU X, et al . Research progress of thermal protection technique by active mass injection for hypersonic vehicle[J ] . Acta Aerodynamica Sinica, 2022 , 40 ( 6 ): 1 − 13 (in Chinese).

YE Y D, ZHANG H X, JIANG Q X, et al . Some key problems in the study of aerodynamic characteristics of near-space hypersonic vehicles[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2018 , 50 ( 6 ): 1292 − 1310 (in Chinese).

ZHU G S, YAO S Y, DUAN Y . Research progress and engineering application of flow control technology for drag and heat reduction of high-speed vehicles[J ] . Acta Aeronautica et Astronautica Sinica, 2023 , 44 ( 15 ): 1 − 16 (in Chinese).

LI J H, JIN X H, LIU C F, MIAO W B. Experimental and computational study of micro-aerodynamics across different flow regions [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44 (6): 127072 (in Chinese).

ZHU G S, DUAN Y, YAO S Y, et al . Effects of wall mass injection on drag and heat reduction characteristics of high-speed flight vehicles[J ] . Acta Aerodynamica Sinica, 2023 , 41 ( 8 ): 59 − 70 (in Chinese).

KING H H, TALBOT L . Effect of mass injection on the drag of a slender cone in hypersonic flow[J ] . AIAA Journal, 1964 , 2 ( 5 ): 836 − 844 .

MARVIN J G, AKIN C M . Combined effects of mass addition and nose bluntness on boundary-layer transition[J ] . AIAA Journal, 1970 , 8 ( 5 ): 857 − 863 .

DEMETRIADES A, LADERMAN A J, VON SEGGERNL, et al . Effect of mass addition on the boundary layer of a hemisphere at Mach 6[J ] . Journal of Spacecraft and Rockets, 1976 , 13 ( 8 ): 508 − 509 .

WIMBERLY C R, MEGINNIS F K . Transpiration and film cooling effects for a slender cone in hypersonic Flows[J ] . AIAA Journa1, 2003 , 8 ( 6 ): 1032 − 1038 .

FANG Y C, LIOU W W, XU S X . Skin friction prediction for high-speed turbulent boundary layers with ablation[J ] . Journal of Spacecraft and Rockets, 2004 , 41 ( 5 ): 893 − 895 .

OLYNICK D, CHEN Y K, TAUBER M. Forebody TPS sizing with radiation and ablation for the Stardust Sample Return Capsule [C ] // AIAA 32 nd Thermophysics Conference. Atlanta: AIAA, 1997-2474.

CHEN Z, YU C P, LI X L, et al. Effect of uniform blowing or suction on hypersonic spatially developing turbulent boundary layers[J]. Science China Physics, Mechanics Astronomy, 2016, 59(6): 664702.

SU S Y, SHI Y L, LIU S, et al. Numerical study on the effect of head mass ejection on aerodynamic heating[C]// Proceedings of the 19th National Hypersonic Aerodynamic/Thermal Symposium, 2020 (in Chinese).

WANG L Y, TAN M J, WANG Z F, et al . Impact of low speed ejection on aerodynamic heating of hypersonic aircrafts[J ] . J ournal of Nanjing University of Aeronautics Astronautics, 2019 , 51 ( 4 ): 503 − 511 (in Chinese).

XIAO Y, SHI Y L, SU S Y. Study of mass injection effects on hypersonic boundary layer[C]// 19th China Aerodynamics Physics Aerodynamics Academic Exchange Conference. 2019: 142-126 (in Chinese).

阎超. 计算流体力学方法及应用[M]. 北京: 北京航空航天大学出版社, 2006.

MIAO W B, LUO X G, CHENG X L, et al . Surface recombination effects on aerodynamic loads of hypersonic vehicles[J ] . Acta Aerodynamica Sinica, 2014 , 32 ( 2 ): 235 − 239 (in Chinese).

LIOU M S. A further development of the AUSM+ scheme towards robust and accurate solutions for all speeds[C]// 16th AIAA Computational Fluid Dynamics Conference, Orlando, Florida. Reston, Virginia: AIAA, 2003.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Research status of aerodynamic design for integrated propulsion and airframe in near-space high-altitude long-endurance (HALE) UAVs

Aerodynamic characteristics of Gurney flaps under special atmosphere

Preface to the column on “New-Generation Wind Power Aerodynamics”

Accuracy-preserving algorithm for difference schemes applied to non-uniform grids

Analysis of lift enhancement, drag and noise reduction characteristics of oscillating jets on aircraft figh-lift devices

Related Author

GAN Wenbiao

GUAN Chenxi

ZHUANG Junjie

XIANG Jinwu

CUI Zhao

XIE Qiang

ZHANG Hua

HAN Dong

Related Institution

Research Institute of Unmanned System, Beihang University, Beijing

School of Aeronautic Science and Engineering, Beihang University , Beijing

Aircraft Flight Test Technology Institute, Chinese Flight Test Establishment

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics

AI问答

⁰