Abstract
Near field screech tone analysis of a typical underexpanded low supersonic circular jet issuing from sonic nozzle have been carried out numerically through solving axisymmetric Navier-Stokes equations directly. Screech tones’s spectral information and the dynamic evolution of their corresponding flow structures and acoustic field are presented. Numerical results indicate that axisymmetric A1 mode and A2 mode screech tones are generated at the trailing edges of fourth and third shock-cell respectively. It is also found that screech tone’s generation is associated with the compressive regions outside jet shear layer closely.
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Li, H., Luo, Y., Zhang, S.H. (2019). Numerical Study of Shock-Associated Noise in Axisymmetric Supersonic Jet. In: Zhou, Y., Kimura, M., Peng, G., Lucey, A., Huang, L. (eds) Fluid-Structure-Sound Interactions and Control. FSSIC 2017. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-10-7542-1_53
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DOI: https://doi.org/10.1007/978-981-10-7542-1_53
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