چكيده به لاتين
Abstract:
Micro Vortex Generators are small aerodynamic devices that generally have height around the size of the boundary layer, and, by the instalation of their arrays on the wing surface, due to increasing the momentum of flow, the flow separation be delayed. Therefore, the force of the compression force decreases and will increase the maximum coefficient. Therefore, the compression drag will be reduced and the maximum lift coefficient will be exceeded.
In this thesis, a numerical study of the effect of micro vortex generators on aerodynamic coefficients and stall angle of a three-dimensional wing with NACA 0018 airfoil has been investigated. This numerical study was performed using the ANSYS FLUENT 16 software and by the K-Epsilon Realizable Turbulence Model.
In this numerical work, the effect of two types of micro vortex generators with two different heights installed in different positions of the longitudinal and at different angles of attack and in streams with different Mach numbers for Doubles with the aspect ratio of 7 and 5 is discussed. In the results, it was found that increasing the Mach number would increase the effect of micro vortex generators. It was also found that as the angle of attack increases, the optimal installation location of micro vortex generators will be more spaced along the longitudinal of the wing leading edge. In general, micro vortex generators, regardless of their location, except at small angles of attack that increase insignificant drag force, reduce drag force, increase the maximum lift coefficient and stall angle.
Keywords: Micro vortex generator, three-dimensional wing, Stall Angle, Aerodynamic Coefficients, NACA 0018
