Impact of incident Mach wave on supersonic boundary layer

A. V. Vaganov, Yu G. Ermolaev, G. L. Kolosov, A. D. Kosinov, A. V. Panina, N. V. Semionov, A. A. Yatskikh

Research output: Contribution to journalArticlepeer-review

25 Citations (Scopus)


Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.

Original languageEnglish
Pages (from-to)43-48
Number of pages6
JournalThermophysics and Aeromechanics
Issue number1
Publication statusPublished - 1 Jan 2016


  • boundary layer
  • experimental studies
  • flat plate
  • hot-wire anemometry
  • sharp and blunt leading edges
  • supersonic velocities
  • wind tunnel


Dive into the research topics of 'Impact of incident Mach wave on supersonic boundary layer'. Together they form a unique fingerprint.

Cite this