The comparison of an analytical, experimental, and simulation approach for the average induced velocity of a dielectric barrier discharge (DBD)

Iskandar²,

et al. 2022

ASIIMETRIK

Self Cite

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.

Section: Introductionmentioning

confidence: 99%

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

Iskandar²,

et al. 2022

ASIIMETRIK

Self Cite

“…The Co-flow Jet is a flow control device that can significantly positively impact the airfoil. Co-flow jets can be classified as active flow control devices [11] [12].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics Improvement of NACA 0015 by Using Co-Flow Jet

Iskandar²,

2022

IJMEIR

⎯ this study analyzes co-flow as active flow control in the object of the airfoil. NACA 0015 is the airfoil used in this study. The airfoil was then modified to add co-flow jet features. Co-flow jet was placed on the upper chamber to analyze its effect on airfoil performance. Further, the Co-flow jet was studied by varying the injected mass flow rate ( m ) in the injection slot. The variation of m is 0.15, 0.20, and 0.25 kg/s. The study used CFD with the governing equation RANS. Reynolds Averaged Navier Stokes combined with turbulence model to solve all equations. Two equations for the turbulence model are used in this study. Specifically, this study discusses the aerodynamics of the airfoil, i.e., lift force, drag force, and fluid flow visualization, such as pressure contour and velocity contour. Co-flow jets can improve the aerodynamics of airfoils. The bigger the m injected, the higher the lift coefficient increases. On the other hand, the drag force will be reduced as the number of injected fluid flow increases. Because of that, the airfoil efficiency will be better if using a co-flow jet. However, the Cl/Cd curve peak shifts to smaller as the injection fluid flow are bigger. The fluid flow visualization by velocity contour on AoA=20° revealed that the co-flow jet could overcome separation. Keywords⎯ co-flow jet, mass flow rate, aerodynamic performance, NACA 0015.

“…On the plane, this stall condition can cause the plane to experience a significant loss of lift and can cause the plane to experience a free fall. Various flow control devices can overcome fluid flow separation [7] [8]. Optimization of the use of flow control devices is very dependent on the location of the fluid flow separation point [9] [10].…”

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

Iskandar²,

et al. 2022

mesin

Self Cite

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.