Abstract

The evolution of the artificial wave packet in the supersonic boundary layer of swept wing was experimentally studied for the first time by hot-wire measurements. The localized disturbances were generated by pulse glow discharge. Analysis of the mean flow, integral dependences, the averaged waveforms of wave packet and spectral data analysis in supersonic boundary layer of swept wing has been executed. Estimates of the velocity of propagation of controlled disturbances downstream are made. A comparison of the wave packet development in the boundary layer of a swept wing at two Mach numbers is given.

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