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, James W.; Iskandar, Waridho; Wahyuni, Fitri; Ferdyanto, Ferdyanto

doi:10.23917/mesin.v23i2.18217

Cited by 8 publications

(4 citation statements)

References 18 publications

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“…All dimensions are shown in the form of multiplication of the values of c. The symbol c is the length of the airfoil chord [19]. In this study, the chord length of NACA 0015 and NACA 4415 is 1 meter [20]. The final form of NACA 4415 and NACA 0015 after modification can be seen in Figure 3.…”

Section: B Modification Of Airfoilsmentioning

confidence: 94%

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Julian

Iskandar

Wahyuni

2023

IJMEIR

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⎯ This research modifies the leading-edge structure of NACA 0015 and NACA 4415 to resemble the nose of a beluga whale. The focus of this modification is to improve the airfoil's aerodynamic performance and investigate the changing fluid flow patterns. Numerical equation used is RANS combined with the k-ε turbulence model. Mesh independence test shows that mesh with 200 elements is the best mesh. Validation results reveal that CFD data can follow the trend of experimental data, especially on the AoA before the stall. There was a significant increase in Cl from NACA 0015 and NACA 4415 at AoA>9°. On the other hand, the modification also had a positive effect by lowering the Cd value. The modification also provides an advantage by increasing the maximum Cl/Cd value. Furthermore, the separation point data shows that the modification can delay the separation of the fluid flow in the airfoil. Modifications can cause an increase in pressure on the lower side and a decrease in pressure on the upper side. Through velocity contours and streamlines, the modifications can reduce the recirculation area. Overall, modifying the leading edge has positive impacts on the NACA 0015 and NACA 4415 airfoils.

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Section: B Modification Of Airfoilsmentioning

confidence: 94%

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Julian

Iskandar

Wahyuni

2023

IJMEIR

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“…The boundary conditions of a fluid system serve to determine the boundaries of computational domain, replicating real-world experimental conditions in simulations. The domain is characterised by two distinct boundary conditions in this study, with the centre of a circular field lying at the trailing edge of an airfoil (Julian, Iskandar, Wahyuni and Ferdyanto, 2022). The first part of the domain will be configured as a velocity inlet with the velocity of 21.9 m/s.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Numerical Modelling of NACA 0015 Airfoil Under the Erosion Condition

Rayhan Fariansyah Billad,

James Julian,

Fitri Wahyuni

et al. 2024

ASIIMETRIK

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Airfoil that experiences erosion caused by flying debris that hit the airfoil can affect the performance of the airfoil. This research was studied to determine the effect of erosion with varying erosion length using numerical methods on the performance of the NACA 0015 airfoil. This research was simulated using the Computational Fluid Dynamics (CFD) approach. Reynolds Averaged Navier-Stokes (RANS) is implemented as the governing equation. The turbulence model used in this research is the k-epsilon model. The Reynolds number used is 1.5 x 10⁶. This research proves that the erosion effect can reduce the Cl value and increase the Cd value on the NACA 0015 airfoil. Increasing the erosion length on the airfoil can also affect the Cl value and Cd value, but this effect is insignificant. In the contour visualization, it can be seen that the airfoil that is experiencing erosion has a pressure contour that increases in the upper chamber and decreases in the lower chamber compared to the airfoil that does not experience erosion so that it can reduce the lifting force of the NACA 0015 airfoil. The flow velocity and streamline contours also show greater circulation in the erosion airfoil, which can accelerate the stall by 1o AoA. Then, variations in increasing erosion length on the airfoil do not show any significant differences in pressure contours or circulating flow.

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“…Therefore, the Reynolds Averaged Navier-Stokes (RANS) equation is used as the Governing equation. The RANS equation consists of continuity and momentum equations of fluid flow which are functionally modified for CFD applications [13]- [15]. The RANS equation can be seen mathematically in Equations ( 2) and (3)…”

Section: Governing Equationmentioning

confidence: 99%

The Influence of Fillet Step on Backward-Facing Step Flow Characteristics

Julian,

Anggara,

Wahyuni

2023

infotekmesin

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Backward-facing step (BFS) is a model that provides several applicative features in engineering. The complex phenomena of BFS flow have a crucial impact on any application. Therefore, this study comprehensively investigates the flow characteristics of BFS with various step shapes. The backward-facing step (F-BFS) fillets were tested at intervals of Reynolds number 50 smaller than Re smaller than 400 using the CFD approach. Based on the computational results, it was found that flow separation is a fundamental phenomenon in BFS flow. Due to sudden expansion, Flow separation forms a recirculation area which continues to increase almost linearly with an increase in the Reynolds number. The recirculation area contains unstable rotating vortexes, which can impact the flow efficiency of BFS. Using a different step shape proves that F-BFS can minimize the recirculation area to increase the efficiency of the BFS flow.

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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

Cited by 8 publications

References 18 publications

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale

Numerical Modelling of NACA 0015 Airfoil Under the Erosion Condition

The Influence of Fillet Step on Backward-Facing Step Flow Characteristics

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