Akademik Veri Yönetim Sistemi
The 5th International Conference of Materials and Engineering Technology (TICMET'23), Trabzon, Türkiye, 13 - 16 Kasım 2023, ss.278-285
The experimental study aims to investigate the effects of backward counter-rotating vortex
generator (VG) pairs on the suction surface of NACA 0012 airfoil at angles of attack between 0°
and 30°. Experiments were carried out with the help of force measurements in a wind tunnel for
Re = 6×104 at different chordwise directions that are x/c = 10%, 20%, 30%, 40%, and 50%. The
NACA 0012 airfoil model has a chord of 150 mm and a spanwise of 300 mm. The dimensions of
the VGs are chosen to be a length of 15 mm, a height of 5 mm, a distance between 5 mm, a
distance between pairs (λ) of 30 mm and an angle of (β) VG () of 10 °. Vortex generators
delayed the stall angle and enhanced the post-stall characteristics compared to the baseline
model. The maximum lift coefficient (CLmax) of the airfoil with VGs at x/c = 10% and 20% is
reached up to 6.15% compared to the baseline model. Compared with the baseline model, the
models with VGs postponed the stall angle up to 2⁰ at x/c = 10% and 1⁰ at x/c = 20%, 30%, and
40%. VGs at x / c = 10%, 20% and 30% have increased because they are close to the airfoil's
leading edge in the prestall region.