Drag reduction due to recirculating bubble control using plasma actuator on a squareback model

Karim, Riza Farrash; Julian, James W.

doi:10.1051/matecconf/201815401108

Cited by 7 publications

(5 citation statements)

References 11 publications

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“…It is this Cl that causes the airfoil to have the ability to fly. The Cd has a vector in the same direction as the freestream velocity (Julian et al, 2016;Karim and Julian, 2018). Mathematical calculations for Cd and Cl are shown by equations 5 and 6 (Alom, Borah and Saha, 2018).…”

Section: Coefficient Lift and Coefficient Dragmentioning

confidence: 99%

Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods

Julian,

Siswanto,

Wahyuni

et al. 2023

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This study was conducted using the Computational Fluid Dynamics (CFD) method using the Reynolds Averaged Navier Stokes (RANS) approach. The type of airfoil used in this study is the asymmetry NACA 4415 airfoil type. In this paper, computational tests were carried out on the airfoil with the addition of bionic flaps on its trailing edge. This study's update tests three variations of the Reynolds number: Re = 106, Re = 5 × 105, and Re = 3 × 105. The airfoil test was carried out at AoA 0°–25°. The addition of bionic flaps causes a decrease in lift performance at low AoA, but at high AoA, it can increase lift performance on airfoils. In addition, adding a bionic flap on the airfoil can delay the occurrence of a stall. At AoA 10°–13°, the Cd of the three variations of the Reynolds number experiences an increase in performance. Then, from this computational test, the resulting Coefficient moment (Cm) is a pitch down because the torque is below zero.

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Section: Coefficient Lift and Coefficient Dragmentioning

confidence: 99%

Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods

Julian,

Siswanto,

Wahyuni

et al. 2023

ASIIMETRIK

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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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“…Because of their ability to generate lift, airfoils are used in aircraft, wind turbines, MAVs, and UAVs . The lift capacity of an airfoil is usually expressed in dimensionless units known as the lift coefficient (Cl) [5]. Cl data is usually presented in the curve of the change of Cl with the angle of attack (𝛼).…”

Section: Introductionmentioning

confidence: 99%

“…This study aims to provide a new method for determining the location of fluid flow separation at a low Reynolds number. Low Reynolds number ranges from 10 4 to 310 5 . The proposed method is to plot the Cf curve along the upper side of NACA 0015.…”

Section: Introductionmentioning

confidence: 99%

Computational Fluid Dynamics Analysis Based on the Fluid Flow Separation Point on the Upper Side of the Naca 0015 Airfoil With the Coefficient of Friction

Julian

Iskandar²,

Wahyuni³

et al. 2022

mesin

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A new method that is more practical, efficient and applicable is proposed to track the position of fluid flow separation on the upper side of NACA 0015. The proposed method is the coefficient of friction curve (Cf) method on the airfoil's upper side. The approach used is a computational fluid dynamics (CFD) approach. The governing equation used is the Reynolds Averaged Navier-Stokes (RANS) equation. is the turbulence model implemented in this study. The research is conducted on the low Reynolds number category. The low Reynolds number is in the range of values from 104 to 3Í105. Cf can predict the location of fluid flow separation more practically, efficiently, and applicable than the fluid flow velocity profile method. Flow separation begins to form at =8° at position x/c=0.8. The location of the fluid flow separation continues to move closer to the leading edge as the airfoil increases. Through the Cf curve, the location of the fluid flow separation is when the Cf curve experiences a sudden decrease and approaches the x-axis. If the separation points are described in the form of velocity profiles and fluid flow velocity contours, it will form an extreme decrease.

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Drag reduction due to recirculating bubble control using plasma actuator on a squareback model

Cited by 7 publications

References 11 publications

Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods

Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods

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

Computational Fluid Dynamics Analysis Based on the Fluid Flow Separation Point on the Upper Side of the Naca 0015 Airfoil With the Coefficient of Friction

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