Heat flux measurement at hypersonic turbulent separated flow field induced by the blunt fins
Year: 2024
Type: conference-paper
Abstract: 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.
Authors: Jikui Ma, Yaofeng Liu, Yuwei Liu, Jun Shi
Institution: China Academy of Aerospace Aerodynamics
Language: English
Subfield: Computational Mechanics
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W4404267037