Passive Flow Control over Naca0012 Aerofoil using Vortex Generators

Gopinathan, V. T.; Ganesh, M. Ashwin

doi:10.17577/ijertv4is090634

Cited by 3 publications

(2 citation statements)

References 10 publications

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“…Optimal drag coefficient was obtained taking into account several parameters such as the VG height, the position from the leading edge and the aperture. The effects of VG attached at different locations and at various attack angles have been studied by Gopinathan et al (2015), Kumar et al (2016) and Agarwal et al (2016). They found that at small attack angles, the VG have insignificant effects with a small decrease in the lift force and a small increase in the drag force.…”

Section: Introductionmentioning

confidence: 99%

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

Hares¹,

Mébarki²,

Brioua³

et al. 2019

JSSCM

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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.

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Section: Introductionmentioning

confidence: 99%

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

Hares¹,

Mébarki²,

Brioua³

et al. 2019

JSSCM

View full text Add to dashboard Cite

show abstract

“…Near wall flow is better able to withstand adverse pressure by increasing flow turbulences, which reduce likelihood of secondary flow. It will make an effort to increase the turbulence flow by adding a turbulent generator to the supporting area [10]. A type of turbulent generator known as a vortex generator (VG) is shaped like fins.…”

Section: Introductionmentioning

confidence: 99%

Effect of Vortex Generators on Airfoil NACA 632-415 to Aerodynamic Characteristics Using CFD

Permatasari

Widyawati²

2023

IJEEPSE

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To determine the aircraft’s flight performance, the airfoil type must be considered when designing the wing. A vortex can form when the airfoil travels through a fluid stream with a difference in velocity and pressure around it. Airfoil modification is carried out to delay the occurrence of flow separation by adding a vortex generator. This paper discusses how adding the vortex generator helps slow the stall’s onset and how the vortex generator affects the fluid flow and aerodynamic forces acting on the NACA 632-415. The vortex generator profile is positioned at an x/c = 20% of the chord line’s direction from the leading edge. The variation used is an airfoil’s angle of attack (α). Some parameters to be evaluated include the coefficient lift force (CL), the coefficient drag force (CD), and the gliding ratio (CL/CD). The research was conducted by the CFD method based on the angle of attack that produces the coefficient lift and drag forces. The addition of the vortex generator can delay the flow separation, increase the lift force coefficient by about 24.9%, the drag force coefficient by about 2.7%, and the gliding ratio by 9.1%.

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Investigation of aerodynamic performance of Clark-Y airfoil with more realistic tubercle model and internal slots

2023

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An experimental study is conducted to research the combined effect of leading-edge (LE) tubercles and internal slots on the Clark-Y airfoil at Reynolds numbers (Re) of 5.0×104, 7.5×104, and 1.0×105 for angles of attack ranging from 0° to 30°. The Clark-Y is a cambered airfoil that performs well at low and medium Reynolds numbers, having a maximum thickness of 11.7% at 28% of the chord. Five different test models are the subjects of experiments, one of which is the baseline. The other test models are the Wavy model, which has LE tubercles, and the Wavy with three different slot positions: the Wavy-LES (leading-edge slot), the Wavy-MS (middle slot), and the Wavy-TES (trailing-edge slot). The LE tubercle geometry is formed by the sum of two sinusoidal wave functions with a realistic approach. In the present work, experimental studies are performed through force measurements, and detailed information on a 3-dimensional flow field is obtained by a surface-oil flow visualization technique. Force measurements indicate that the Wavy model delays stall and exhibits smoother stall behavior compared to the baseline. Moreover, the findings show that the lift coefficient (CL) of the Wavy model deteriorates in the pre-stall region with the inclusion of the internal slots but improves significantly in the post-stall region. Maximum improvement in CL in the post-stall region was achieved by 60% in Wavy-LES at Re of 5.0×104 as compared to the baseline. At Re of 5.0×104, Wavy and Wavy-MS present a better lift-to-drag ratio (CL/CD) than the other models in the pre-stall region, whereas the baseline is the best at Re of 1.0×105. The best CL/CD is achieved by Wavy-LES in the post-stall region, regardless of the Reynolds numbers. The variation of flow characteristics relevant to aerodynamic performance is revealed by surface oil flow visualization for all tested models.

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Passive Flow Control over Naca0012 Aerofoil using Vortex Generators

Cited by 3 publications

References 10 publications

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

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

Effect of Vortex Generators on Airfoil NACA 632-415 to Aerodynamic Characteristics Using CFD

Investigation of aerodynamic performance of Clark-Y airfoil with more realistic tubercle model and internal slots

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