Heat flux measurement at hypersonic turbulent separated flow field induced by the blunt fins

Hypersonic separated flow induced by the protrusions is one of the most concerning research studies in aerodynamics due to the complex flow structure and the significance of engineering. An experimental study of three-dimensional hyper-sonic separated flow induced by the blunt fins is investigated....

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Bibliographic Details
Published in:Journal of physics. Conference series 2024-11, Vol.2882 (1), p.12099
Main Authors: Ma, Jikui, Liu, Yaofeng, Liu, Yuwei, Shi, Jun
Format: Article
Language:English
Subjects:
Fins
Flow separation
Heat flux
Heat transfer
Mach number
Shock waves
Sweep angle
Three dimensional analysis
Three dimensional flow
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Summary:Hypersonic separated flow induced by the protrusions is one of the most concerning research studies in aerodynamics due to the complex flow structure and the significance of engineering. An experimental study of three-dimensional hyper-sonic separated flow induced by the blunt fins is investigated. The tests are performed with inflow Mach number 6. The main flow properties of the shock systems are described by analyzing Schlieren photographs. The heat flux data are obtained by using high precision platinum film sensors. The effects of the fin sweep angle are also presented. Results show that the maximum heat flux decreases, and the range of the separation zone quickly reduces as the swept angle increases. Low-frequency oscillations of separated flow fields are analyzed through instantaneous heat flux signals at typical measuring points. It is shown that characteristic frequencies of shock wave oscillation with no rear sweep angle is about 1 k Hz.
ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/2882/1/012099