Oscillating shock impinging on a flat plate at mach 6

Gaetano M.D. Currao, Liam P. McQuellin, Andrew J. Neely, Fabian Zander, David R. Buttsworth, Jack J. McNamara, Ingo Iahn

研究成果: Conference contribution

10 引文 斯高帕斯(Scopus)


This work discusses the design, measurement and simulation of an experiment in a Mach 6 wind tunnel involving an oscillating shock impinging on a flat plate. The design of the oscillating shock-generator is performed using piston theory. The oscillation frequency is designed to be larger than 30 Hz, to match typical fuselage natural frequencies of hypersonic vehicles and technology demonstrators, such as the X-33 and the X-43. The shock generator is free to pitch, resulting in a shock that varies in intensity and impingement point, with a maximum flow deflection angle of 10 degrees. Transition appears to take place just downstream the separated region for both static (with a fixed flow deflection angle) and dynamic experiments. Transition decreases the peak pressure levels while determining a rise in the heat-flux distribution. The motion of the reattachment point appears to lag behind the numerical predictions by a fifth of the oscillation period. Görtler-like vortices are observed in the reattachment region; while their magnitude is a function of the shock strength, their spanwise distribution appears to be unaffected by the motion of the shock generator.

主出版物標題AIAA Aviation 2019 Forum
發行者American Institute of Aeronautics and Astronautics Inc, AIAA
出版狀態Published - 2019
事件AIAA Aviation 2019 Forum - Dallas, United States
持續時間: 2019 6月 172019 6月 21


名字AIAA Aviation 2019 Forum


ConferenceAIAA Aviation 2019 Forum
國家/地區United States

All Science Journal Classification (ASJC) codes

  • 電腦科學應用
  • 電氣與電子工程
  • 航空工程


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