Effect of plasma actuator in boundary layer on flat plate model with turbulent promoter

Julian, James W.; Harinaldi,; Budiarso,; Wang, Chin-Cheng; Chern, Ming‐Jyh

doi:10.1177/0954410017727301

Cited by 14 publications

(8 citation statements)

References 10 publications

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“…Another type of fluid flow separation on the upper side of the airfoil is peeling off the airfoil's boundary layer. This type of fluid flow separation is often found in medium and high Reynolds numbers (Julian et al, 2018).…”

Section: Introductionmentioning

confidence: 90%

Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Julian

Iskandar²,

Wahyuni³

et al. 2022

ASIIMETRIK

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The computational study discusses the application of the co-flow jet technique as a fluid flow control device on the NACA 0015 airfoil. The numerical equation used is the RANS equation with the k-ε turbulence model. There are three variations of the mesh proposed in this paper. The first variation is a fine mesh with 100,000 elements. The second variation is a medium mesh with 50,000 elements. Meanwhile, the third variation is coarse mesh with 25,000 elements. Based on the mesh independence test results, the mesh with the lowest error value is the fine mesh. Co-flow jet is proven to control fluid flow on the upper side of NACA 0015. Co-flow jet can also improve the aerodynamic performance of NACA 0015 by increasing Cl and decreasing Cd. The increase in Cl was 114% and the decrease in Cd was 24%. The fluid flow separation on the upper side of the airfoil can also be handled well by the co-flow jet.

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Section: Introductionmentioning

confidence: 90%

Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Julian

Iskandar²,

Wahyuni³

et al. 2022

ASIIMETRIK

Self Cite

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“…This numerical method uses the Reynolds Averaged Navier-Stokes (RANS) equation. It equation is a modified equation for CFD applications [16], [17]. Mathematically, equations ( 1) and (2) represent the RANS equation.…”

Section: Numerical Methods and Turbulence Modelmentioning

confidence: 99%

Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

Julian,

Anggara,

Wahyuni

2023

IJMEIR

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⎯ Airfoil is a fundamental geometry in designing various aerodynamic objects. Passive flow control installation is essential in determining the airfoil's aerodynamic performance. The influence of variations in slat size as a passive flow control instrument is analyzed using the CFD method with a Reynold number of = 6 Re 10 . In this study, NACA 6641 was seleceted as slat. The slat has two variations, i.e., 10% and 16% of the chord length. Based on the computational results, variations in slat size have a substantial influence on the aerodynamic efficiency of the airfoil. Variations in slat size additional Cl ability to reach 20.6043% and 13.1917%, respectively. In addition, a 16%c slat can delay a stall until it reaches AoA ≥ 19°. Meanwhile, a 10%c slat can delay a stall until it reaches AoA ≥ 17°. Variations in slat size also affect the drag force. Slat measuring 16%c can addition Cd up to 50.9252%. Meanwhile, 10% c slat additional Cd up to 21.8389%. Based on the resulting lift-to-drag ratio curve, a 10%c slat has the lowest lift-to-drag ratio compared to a 16%c slat. However, a 10%c slat has the highest level of stability when compared to a 16%c slat installation and without a slat installation.

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“…This equation is generally used in CFD applications with numerical methods. The RANS equation can be seen in equations 1 and 2 (Aftab et al, 2016;Harinaldi et al, , 2016Julian et al, 2016Julian et al, , 2018Harinaldi et al, 2020;Karim and Julian, 2018;Julian et al, 2017). Equation 1represents the continuity equation of the fluid flow.…”

Section: Governing Equation and Turbulence Modelmentioning

confidence: 99%

The The Effect of Micro Geometry with Various Forms as Passive Flow Control in NACA 4415

Julian,

Anggara,

Wahyuni

et al. 2023

ASIIMETRIK

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This study investigates the effect of variations in the micro geometry with various forms as passive flow control devices on the aerodynamic capability of the airfoil. Micro-cylinder, micro-slat, and micro-cube are installed close to the leading edge of the NACA 4415 airfoil as a micro geometric variation of passive flow control devices with a predetermined diameter of 3% c located at coordinates x= 0% c and y= 8 %c of the leading edge of the airfoil. The Reynolds number used in this study is Re = with AoA variations from 0°-30°. This study's results show a decrease in Cl of 12% with a micro-cylinder, 26% with a micro-slat, and 28% with a micro-cube. In addition, the Cd produced by using the variation of the device micro geometry has increased significantly. Thus, the final result is a lift-to-drag ratio of more petite than the without micro. In the streamlined contour shown when the airfoil is at a high angle of attack, the use of micro geometric variations of passive flow control devices can have an effect that causes reduced recirculation that occurs in the airfoil. However, the impact of these devices is not optimal, resulting in a reduction in the aerodynamic capability of the NACA 4415 airfoil.

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Effect of plasma actuator in boundary layer on flat plate model with turbulent promoter

Cited by 14 publications

References 10 publications

Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Characterization of the Co-Flow Jet Effect as One of the Flow Control Devices

Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance

The The Effect of Micro Geometry with Various Forms as Passive Flow Control in NACA 4415

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