I.A. Znamenskaya, D.F. Latfullin, I.V. Mursenkova
Moscow State University

Visualization of the laminar-turbulent transition in the supersonic boundary layer at initiation of the pulse s surface discharge

The structure of near boundary air flows at subsonic and supersonic velocities in the shock tube by visualization by a radiation of the pulse surface distributed discharge of nanosecond duration (plasma sheet) is experimentally investigated. Difference in structure of a luminescence of a plasma layer is shown at a laminar and turbulent mode of boundary layer. Position of area of laminar-turbulent transition is defined at Mach numbers of the flow to 1,6, density of 0,06-0,45 kg/m3 and are estimated Reynolds's critical numbers of transition (2 – 4)•105.
Full paper pdf