Experimental Studies of the Impact of Periodic Modulation of the Flow on the Development of Disturbances in the Boundary Layer of a Swept Wing at a M = 2.5

Read more Abstract
The results of experimental studies on the impact of periodic flow modulation on the development of natural disturbances and artificial localized wave packets in the boundary layer of a swept wing with a leading edge swept angle of 40 degrees at a Mach number M = 2.5 are presented. The boundary layer was modulated using periodic roughness on the model surface. Artificial wave packets were generated by a pulsed glow discharge. Hot-wire anemometer measurements showed that, according to the experimental conditions, periodic modulation of the boundary layer leads to the stabilization of the development of controlled localized disturbances and to an increase in the growth of natural disturbances.

Keywords
experiment, supersonic flow, hot-wire anemometer, laminar-turbulent transition, turbulence, boundary layer, swept wing
Funding
The research was carried out within the framework of the Program of Fundamental Scientific Research of the state academies of sciences in 2013-2020 (project No. AAAA-A17-117030610125-7) and was supported by the Grant of the President of the Russian Federation (MK-2491.2019.1). The study was conducted at the Joint Access Center “Mechanics” of ITAM SB RAS
УДК 532.526

Experimental Studies of the Impact of Periodic Modulation of the Flow on the Development of Disturbances in the Boundary Layer of a Swept Wing at a M = 2.5