Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehi
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Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: [email protected]
Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle Bin-xian SHEN1,2, Hong-peng LIU†‡2, Wei-qiang LIU2 1
China Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China 2
Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China †
E-mail: [email protected]
Received Nov. 14, 2019; Revision accepted Apr. 18, 2020; Crosschecked July 15, 2020
Abstract: Flying condition with angle of attack is inevitable in a hypersonic vehicle, and it may influence the thermal protection system (TPS) performance of opposing jet and its combinations. A 3D Navier–Stokes equation and shear stress transfer (SST) k-ω model with compressible correction are employed to simulate the angle of attack characteristics of a blunt body with opposing jet and platelet transpiration TPS. The flowfield and heat flux transfer for angles of attack 0°, 3°, 6° with jet pressure ratio PR=0.1 and 0°, 6°, 12° with PR=0.2 are obtained. Numerical results show that the flowfield is no longer symmetrical with the effect of the angle of attack. The flowfield and heat transfer in windward and leeward performed adversely. The recompression shock wave in windward is strengthened, which increases local temperature and strengthens heat transfer. The opposing jet fails in thermal protection when the angle of attack reaches critical value; however, the critical angle of attack can be promoted by increasing PR. Finally, the transpiration gas can strengthen the cooling efficiency of windward, thereby, increasing the critical angle of attack. Key words: Thermal protection; Opposing jet; Platelet transpiration; Angle of attack https://doi.org/10.1631/jzus.A1900514 CLC number: V423
1 Introduction The nose-tip of hypersonic vehicles can experience extreme aerodynamic heating when flying in high speed. Accumulated heating can destroy the structures and flying systems if not effectively dissipated. Therefore, hypersonic vehicles must have an effective and reliable thermal protection system (TPS) to be able to efficiently reach cruise speed. TPS methods for hypersonic vehicles fall into three categories: passive, semi-passive, and active. The material structure and ablation TPS currently applied in real flights belong to the passive and semi-passive ‡
Corresponding author ORCID: Hong-peng LIU, https://orcid.org/0000-0002-1664-7517 © Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2020
methods, respectively (Xie et al., 2013; Riccio et al., 2017). Although the ceramic matrix composites (Ferraiuolo et al., 2019) and hybrid carbon/carbon (C/C) composites (Zhang and Li, 2018) are now used as TPS in some vehicles, these traditional passi
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