Aerodynamic performances improvement of NACA 4415 profile by passive flow control using vortex generators

Abstract

Improvement of the airfoil NACA 4415 aerodynamic performances by flow control using a passive technique was achieved in this study. Gothic-shaped vortex generators were added at the profile upper surface. Vortex Generators (VG) were used to avoid boundary layer separation at the profile trailing edge, thus reducing the drag force and improving aerodynamic performances. A numerical simulation with fluent code was performed. A parametric study was carried out to determine optimal disposition and dimensions of the VG. Six VG parameters were tested; thickness (E), height (H), length (L), aspect ratio (r), incidence angle (α) and the VG position relative to the chord of the profile (XVG). The results show an increase in the lift coefficient for the profile with vortex generators in the range of high attack angles. Optimal dimensions and positions of the VG were obtained.

The Effect of Location and Shape of Vortex Generators on Aerodynamic Characteristics of a NACA 4415 Airfoil

“…[1,2]. Hares et al [3] conducted a comprehensive investigation into the effects of passive flow control using vortex generators (VGs) on the aerodynamic performance of the NACA 4415 airfoil. Through simulations and parameter exploration, the authors identified optimal VG dimensions and positions, resulting in improved lift coefficients, particularly at high angles of attack.…”

Turbulent Flow Control With Vortex Generators Around a Symmetrical Airfoil at High Attack Angles

“…Since the introduction of passive control through vortex generators by Taylor (1947), this technique has been widely used to delay boundary layer separation through parametric studies (Lin. 1999, Godard et al 2006, Zhen et al 2011, Fouatih et al 2016and Hares et al 2019, to improve the wings lift (Nickerson. 1986), avoid or delay separation in subsonic diffusers (Brown et al 1968) and reduce aircraft fuselage drag (Calarese et al 1985).…”