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Concept of non-ablative thermal protection system for hypersonic vehicles
Liu YF(刘云峰); Jiang ZL(姜宗林); Jiang, ZL (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China.
Source PublicationAIAA Journal
2013-03
Volume51Issue:3Pages:584-590
ISSN0001-1452
AbstractIn order to reduce the shock-wave drag and aerodynamic heating of hypersonic vehicles effectively a new concept of non-ablative thermal protection system was proposed based on the idea of flowfield reconstruction. In this non-ablative thermal protection system a spike-blunt body structure and lateral jets are combined together to realize the flowfield modification. The spike transforms the bow shock into a conical shock, and the lateral jets increase the angle of conical shock wave and keep it away from the blunt body to avoid severe shock/shock interactions. Flow visualizations and pressure measurements were conducted in a hypersonic wind tunnel at Mach number 6 to demonstrate this concept. Numerical simulations were also carried out. Both experimental and numerical results demonstrate that the non-ablative thermal protection system works well for shock-wave drag reduction and thermal protection. The peak pressure at the reattachment region is reduced by 65% even under 4 deg attack angle by the lateral jet. Experimental data also show that the working pressure of lateral jets is much lower than that of forward-facing jets at the stagnation point. All the results show that the engineering application of non-ablative thermal protection system appears to be quite promising.
KeywordFlow Fields Flow Visualization Hypersonic Aerodynamics Hypersonic Vehicles Mach Number Shock Waves Thermal Insulating Materials Engineering Applications Experimental Datum Hypersonic Wind Tunnels Numerical Results Stagnation Points Thermal Protection Thermal Protection System Working Pressures
Subject Area空气动力学
DOI10.2514/1.J051875
URL查看原文
Indexed BySCI ; EI
Language英语
WOS IDWOS:000315551200004
WOS KeywordWAVE DRAG REDUCTION ; HEAT-TRANSFER ; ENERGY DEPOSITION ; SUPERSONIC-FLOW ; SHOCK-WAVE ; MITIGATION ; BODIES ; SPIKE ; JET
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace
Funding OrganizationY210061021
DepartmentLHD激波与爆轰物理
Classification一类
Citation statistics
Cited Times:31[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/47144
Collection高温气体动力学国家重点实验室
Corresponding AuthorJiang, ZL (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China.
Recommended Citation
GB/T 7714
Liu YF,Jiang ZL,Jiang, ZL . Concept of non-ablative thermal protection system for hypersonic vehicles[J]. AIAA Journal,2013,51(3):584-590.
APA Liu YF,Jiang ZL,&Jiang, ZL .(2013).Concept of non-ablative thermal protection system for hypersonic vehicles.AIAA Journal,51(3),584-590.
MLA Liu YF,et al."Concept of non-ablative thermal protection system for hypersonic vehicles".AIAA Journal 51.3(2013):584-590.
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