Abstract
We have studied the effect of a porous sound-absorbing insert on the intensity of pressure pulsations in the high-temperature hypersonic flow of carbon dioxide past the surface of a plate oriented at a 10.2° angle of attack. The mode composition of disturbances in the flow core of a pulsed wind tunnel has been experimentally determined, which is dominated by acoustic disturbances of a fast mode. It is established that, under the action of acoustic disturbances of the fast mode on the shock layer, the sound-absorbing insert reduces the intensity of pressure pulsations on the plate surface as compared to a continuous surface. The experimental data are compared to the results of numerical simulations.
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Original Russian Text © I.S. Tsyryulnikov, A.A. Maslov, S.G. Mironov, T.V. Poplavskaya, S.V. Kirilovskiy, 2015, published in Pis’ma v Zhurnal Tekhnicheskoi Fiziki, 2015, Vol. 41, No. 4, pp. 61–67.
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Tsyryulnikov, I.S., Maslov, A.A., Mironov, S.G. et al. The efficiency of the method of sound-absorbing coatings in vibrationally excited hypersonic flow. Tech. Phys. Lett. 41, 184–186 (2015). https://doi.org/10.1134/S1063785015020273
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DOI: https://doi.org/10.1134/S1063785015020273