Passive Control on the NACA 4412 Airfoil and Effects on the Lift

Tebbiche, Hocine; Boutoudj, M.S.

doi:10.1007/978-3-319-17527-0_77

Cited by 5 publications

(2 citation statements)

References 3 publications

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“…It was found that micro vortex generators are very effective to control the flow. Tebbiche et al (2015) studied the effect of a new VG configuration, delta wing shape, placed on line on the suction surface of a curved profile (NACA 4412). The experimental study conducted in a wind tunnel shows an improved lift coefficient with an increase of 20% and one degree delay of the stall incidence.…”

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

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show abstract

“…All of these techniques tend to delay or even eliminate the fluid separation from the wall (Brown et al 1968), increase the lift and reduce drag (Tebbiche et al 2015), optimize energy exchanges, improve comfort and reduce noise.…”

Section: Introductionmentioning

confidence: 99%

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

Tebbiche¹,

Boutoudj²

2019

JSSCM

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The flow on the upper surface of NACA 0015 airfoil is subject to an adverse pressure gradient when the incidence increases. This leads to the boundary layer separation which causes losses in the aerodynamic performances. Control using Vortex Generators (VGs) is a simple passive mean used to delay or eliminate the flow separation from the wall. The two main objectives of the experimental work performed consist in the optimization by experimental design method "DoE" of a new VGs configuration, inspired by Lin's one, by varying its different geometrical parameters. A comparative efficiency study of the two VGs configurations (Lin's VGs, modified VGs) on aerodynamic performances was then undertaken at different Reynolds numbers. In addition to the significant improvement in lift around 22%, the study resulted in a drag reduction of approximately 16% and a stall delay of two degrees. The results were also compared to a three-dimensional numerical simulation (3D-RANS) and showed good agreement. The CFD results highlighted a clear improvement in the momentum thickness along the airfoil's upper face, particularly a rate of 44.44% at 40% of the chord length.

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Numerical investigation and optimization of airfoil flow control using passive air-jet

Aziz¹,

Elsayed

2019

Thermophys. Aeromech.

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Passive Control on the NACA 4412 Airfoil and Effects on the Lift

Cited by 5 publications

References 3 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

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

Numerical investigation and optimization of airfoil flow control using passive air-jet

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