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All Journal Journal of Energy, Mechanical, Material and Manufacturing Engineering Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa Dan Inovasi International Journal of Marine Engineering Innovation and Research
Waridho Iskandar
Universitas Indonesia
Automotive Engineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Electrical & Electronics Engineering Energy Engineering Environmental Science Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Physics Transportation

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Numerical Analysis of Gurney Flap Impact on NACA 4415 Airfoil Aerodynamics Performance James Julian; Mirza Fauzan Lukiano; Fitri Wahyuni; Waridho Iskandar; Nely Toding Bunga
Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 6 Nomor 1 Tahun 2024
Publisher : Fakultas Teknik Universitas Pancasila

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35814/asiimetrik.v6i1.5722

Abstract

Improving airfoil aerodynamic performance is an essential aspect of aerodynamic technology. The use of passive flow control is one way to enhance the aerodynamic performance of the airfoil. The influence of using gurney flaps as passive flow control was explored through the CFD approach employing the RANS control equations with the k-epsilon turbulence model. The airfoil model utilized in this investigation was the NACA 4415 operating at a Reynolds number of 1×106. This study explored three different variations of flap height, namely 0.5%, 1%, and 2% of chord length. The outcomes showed that adding gurney flaps showed quite positive results in increasing the lift and drag performance of NACA 4415. An airfoil with a 0.5%c height flap has an average percentage increase in Cl of 12%, followed by a height flap of 1%c, which is 23%, and a percentage Cl of 37% for a height flap of 2%c. Meanwhile, each variation in height flap affected the increase in Cd. A height flap of 0.5%c increased Cd with an average percentage of 2%, while a height flap of 1%c increased the percentage of Cd by 4% and 6% for a height flap of 2%c. Moreover, visualization of fluid flow with pressure and velocity contours given at AoA 12º to determine the effect on the increase in Cland Cd in NACA 4415.
Numerical Modelling of NACA 0015 Airfoil Under the Erosion Condition Rayhan Fariansyah Billad; James Julian; Fitri Wahyuni; Waridho Iskandar; Nely Toding Bunga
Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 6 Nomor 1 Tahun 2024
Publisher : Fakultas Teknik Universitas Pancasila

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35814/asiimetrik.v6i1.5875

Abstract

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.
Effects of leading-edge defects of the NACA 0015 airfoil on aerodynamic performance with various Reynolds number Ulfa Hanifah Nurhaliza; James Julian; Fitri Wahyuni; Waridho Iskandar
Journal of Energy, Mechanical, Material, and Manufacturing Engineering Vol. 8 No. 2 (2023)
Publisher : University of Muhammadiyah Malang

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.22219/jemmme.v8i2.29400

Abstract

This study investigates and identifies the effects produced by defect on an airfoil when compared to a smooth airfoil. The defect used in this research is of the surface concaved defect (SDD) type, with a deep defect characterized by a smooth sunken deformation. The opening size used is t*=12%, and the equivalent depth of the defect is h*=3%. Computational methods are being used in this research to analyzing flow of the fluid through the NACA 0015 airfoil, both in smooth and defective airfoil, with various Reynolds Number which are 1.6×106, 2×106, and 2.5×106. Standard k-epsilon model is being used in this research as turbulence model. For the smooth airfoil, stall conditions occur at an AoA of 11º, while for the defective airfoil, they occur at an AoA of 9^° for each Re variation. The average decrease in the Cl/Cd ratio from smooth airfoil to defective airfoil at each AoA for all Re variations is 33%. There is an increase in pressure on the upperside leading edge of defective airfoil for all Re values. Based on the velocity streamlines, vortices can be found at the defect cavity, and the vortex at the defective airfoil seems larger than the smooth airfoil.
The Influence of Mounting Angle on Gurney Flap on The Aerodynamics Performance of NACA 0015 Using CFD Method Mirza Fauzan Lukiano; James Julian; Fitri Wahyuni; Waridho Iskandar
International Journal of Marine Engineering Innovation and Research Vol. 8 No. 4 (2023)
Publisher : Department of Marine Engineering, Institut Teknologi Sepuluh Nopember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.12962/j25481479.v8i4.5094

Abstract

Improving the airfoil aerodynamics is quite an essential aspect of the aviation industry. One method for improving airfoil aerodynamics involves applying passive flow control techniques. The effect of using the gurney flap as passive flow control was explored through the CFD approach with the RANS control equation and incorporating k-epsilon as a turbulence model. The airfoil model utilized in this study was the NACA 0015 airfoil operating at a Reynolds number of 1×106. This study explored three different mounting angles of the gurney flap, namely 45°, 60°, and 90°. The outcomes show that adding the gurney flap has positive results in increasing the lift and drag of the NACA 0015. An airfoil with a mounting angle flap of 45° has an average percentage increase in Cl of 23%, followed by a mounting angle flap of 60°, which is 28%, and a percentage Cl of 45% for a mounting angle flap of 90°. Meanwhile, Gurney flaps with a mounting angle of 45° can increase Cd by an average percentage of 3%, while mounting angle flap at 60° increases the Cd percentage by 4% and 5% for a mounting angle of 90°. Moreover, fluid flow visualization with pressure and velocity contours was given at AoA 10º to determine its effect on increasing lift and drag on the NACA 0015 airfoil.
Co-Authors Bunga, Nely Toding Fitri Wahyuni Fitri Wahyuni Fitri Wahyuni James Julian James Julian Mirza Fauzan Lukiano Mirza Fauzan Lukiano Rayhan Fariansyah Billad Ulfa Hanifah Nurhaliza