Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2

A. D. Kosinov, G. L. Kolosov, N. V. Semionov, Yu G. Yermolaev

Результат исследования: Научные публикации в периодических изданияхстатьярецензирование

18 Цитирования (Scopus)

Аннотация

Experimental results are presented on the linear development of a wave train in a three-dimensional supersonic boundary layer on a swept wing with 45°-sweep angle at Mach number M = 2.0. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at frequencies 10 and 20 kHz. The maximum of the controlled pulsation amplitude was localized in the boundary layer in normal to the swept-wing surface direction for spatial amplitude distributions as well as for the amplitude wave spectra. The asymmetry of the wave characteristics of the unstable disturbances in the boundary layer of a swept wing caused by the presence of crossflow is confirmed. The stability characteristics, including dispersion relations and amplification rates over a wide range of wave inclination angles, are obtained for disturbances with prescribed frequencies 10 and 20 kHz.

Язык оригиналаанглийский
Номер статьи064101
ЖурналPhysics of Fluids
Том28
Номер выпуска6
DOI
СостояниеОпубликовано - 1 июн 2016

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