Analysis of Active Flow Control Application in Subsonic Intake Integrated with Aircraft Glider

Abstract

This paper presents the study of subsonic intake, integrated with curvilinear fuselage fore body. Intake’s complex shape leads to the formation of longitudinal vortices causing a significant une-ven distribution of flow parameters at the output section of the intake. Numerical research, using ESI RANS and RANS / ILES methods, of air intake flow were obtain at different throttle modes. The flow fields were compare with the experimental results. Throttling modes with pronounced unevenness at the output section were determined. By means of RANS/ILES methods conducted study of a flow control with synthetic jets in the subsonic intake. The jet’s parameters, which made it possible to reduce the circumferential unevenness by 5 ÷ 39 % at the output section of the intake, were determined.