Panina A.V.   Kosinov A.D.   Semionov N.   Yermolaev Y.G.  

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Reporter: Panina A.V.

The paper presents the results of an experimental study of the controlled pulsations development in the boundary layer of a swept wing at Mach number 2.
The experiments were conducted in T-325 supersonic wind tunnel of ITAM SB RAS at Mach 2 and unit Reynolds number Re1 = 5,1 * 106 м–1. The model of a swept wing with a slightly blunted leading edge was used. Constant temperature anemometer was used for mean and pulsating flow quantities measurements. Artificial disturbance sources based on high frequency glow discharge in chamber were built into the models. Controlled pulsations are delivered into the boundary layers through the surface aperture of 0.5 mm in diameter. The pulsation measurements were synchronized with glow discharge which was ignited with fundamental frequency of 20 kHz. Electrical power of controlled disturbances source was the same in all series of experiments. The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer.
It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and to the strengthening of the oblique breakdown mechanism in the laminar-turbulent transition.

To reports list