{"title":"Study on the interaction mechanism between incident oblique shock wave and transpiration cooling and optimization of porosity","authors":"Xiaojuan Wang, Xiaoqiang Fan, Bing Xiong","doi":"10.1016/j.ast.2025.110154","DOIUrl":null,"url":null,"abstract":"<div><div>Transpiration cooling, due to its high cooling efficiency, is used for thermal protection in hypersonic aircraft. However, oblique shock waves incident on a structural surface can reduce cooling effectiveness, risking thermal protection failure. Additionally, the cooling film changes the wave structure in the main flow, reducing the aerodynamic performance. This study employs numerical methods to analyze the effects of oblique shock waves on transpiration cooling at various shock incidence angles and coolant blowing ratios, as well as the influence of transpiration cooling on the main flow field. The cooling efficiency curve is segmented into four intervals based on the flow mechanisms, with the corresponding optimization objectives proposed. A segmented porosity design method driven by pressure difference is adopted, improving the surface temperature uniformity at the hot end of the transpiration zone by 82.7%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110154"},"PeriodicalIF":5.0000,"publicationDate":"2025-03-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Aerospace Science and Technology","FirstCategoryId":"5","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S1270963825002251","RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q1","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
引用次数: 0
Abstract
Transpiration cooling, due to its high cooling efficiency, is used for thermal protection in hypersonic aircraft. However, oblique shock waves incident on a structural surface can reduce cooling effectiveness, risking thermal protection failure. Additionally, the cooling film changes the wave structure in the main flow, reducing the aerodynamic performance. This study employs numerical methods to analyze the effects of oblique shock waves on transpiration cooling at various shock incidence angles and coolant blowing ratios, as well as the influence of transpiration cooling on the main flow field. The cooling efficiency curve is segmented into four intervals based on the flow mechanisms, with the corresponding optimization objectives proposed. A segmented porosity design method driven by pressure difference is adopted, improving the surface temperature uniformity at the hot end of the transpiration zone by 82.7%.
期刊介绍:
Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to:
• The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites
• The control of their environment
• The study of various systems they are involved in, as supports or as targets.
Authors are invited to submit papers on new advances in the following topics to aerospace applications:
• Fluid dynamics
• Energetics and propulsion
• Materials and structures
• Flight mechanics
• Navigation, guidance and control
• Acoustics
• Optics
• Electromagnetism and radar
• Signal and image processing
• Information processing
• Data fusion
• Decision aid
• Human behaviour
• Robotics and intelligent systems
• Complex system engineering.
Etc.