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Mode decomposition of disturbances in a supersonic flow

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Thermophysics and Aeromechanics Aims and scope

Abstract

Controlled disturbances are inserted into the wind tunnel flow, and probing measurements of the fields of the amplitudes of pressure and phase velocity oscillations of these disturbances are performed. Based on the relations for inviscid interaction of long-wave vortex, entropy, and acoustic disturbances with the shock wave on a wedge and numerical simulations, the coefficients of conversion of various modes to pressure oscillations on the model surface are determined for the test conditions of a supersonic flow in the T-327B blowdown wind tunnel located at the Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences. The method of mode decomposition for controlled disturbances with the use of disturbance conversion coefficients is implemented in the case of a flat plate model with a sharp leading edge aligned at different angles of attack and side-slip in the flow.

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Authors and Affiliations

  1. Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia

    I. S. Tsyryulnikov, Yu. V. Gromyko & T. V. Poplavskaya

Authors
  1. I. S. Tsyryulnikov
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  2. Yu. V. Gromyko
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  3. T. V. Poplavskaya
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Corresponding authors

Correspondence to I. S. Tsyryulnikov, Yu. V. Gromyko or T. V. Poplavskaya.

Additional information

This work was financially supported by the Russian Science Foundation (Grant No. 19-71-00031).

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Tsyryulnikov, I.S., Gromyko, Y.V. & Poplavskaya, T.V. Mode decomposition of disturbances in a supersonic flow. Thermophys. Aeromech. 27, 643–653 (2020). https://doi.org/10.1134/S0869864320050029

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  • DOI: https://doi.org/10.1134/S0869864320050029

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