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All Journal Jurnal Ilmiah Teknologi dan Rekayasa Jurnal Teknologi Media Mesin: Majalah Teknik Mesin Turbo : Jurnal Program Studi Teknik Mesin Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa Dan Inovasi International Journal of Marine Engineering Innovation and Research
Waridho Iskandar
Universitas Pembangunan Nasional Veteran Jakarta
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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Journal : International Journal of Marine Engineering Innovation and Research

 1 
Effect of Single Slat and Double Slat on Aerodynamic Performance of NACA 4415 James Julian; Waridho Iskandar; Fitri Wahyuni; Armansyah Armansyah; Ferdyanto Ferdyanto
International Journal of Marine Engineering Innovation and Research Vol 7, No 2 (2022)
Publisher : Institut Teknologi Sepuluh Nopember

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1410.49 KB) | DOI: 10.12962/j25481479.v7i2.12875

Abstract

This study uses a Computational Fluid Dynamics (CFD) approach. The main object in this study is NACA 4415 with slat variations. The airfoil used as the slat is Eppler 421. Reynolds number in this study is 3Í106. This study uses an unstructured mesh with a triangular cell shape with 137824 elements. The use of slats can improve the aerodynamic performance of NACA 4415. NACA 4415 without slat stalled at AoA=16º. Stall on airfoils with a single slat and double slat occurred at AoA=20º. Slat can increase Cl in NACA 4415; however, the difference in Cl increase is not much different when using a single slat or double slat. An airfoil with a single slat, on average, can increase Cl by 20.9129%. The average increase in Cl for an airfoil with a double slat is 25.6878%. Single slat and double slat increase Cd. A single slat increased Cd with an average increase of 26.1109%, and the average increase in Cd for airfoils with double slat was 54.6152%. Single slat can produce a better Cl to Cd ratio than double slat, but the optimum AoA of double slat is 1º higher than single slat. Visualization of fluid flow at AoA=16° shows the fluid flow separation in the airfoil without a slat. The fluid flow separation can be handled well when NACA 4415 is given a single slat or double slat.
Aerodynamics Improvement of NACA 0015 by Using Co-Flow Jet James Julian; Waridho Iskandar; Fitri Wahyuni
International Journal of Marine Engineering Innovation and Research Vol 7, No 4 (2022)
Publisher : Institut Teknologi Sepuluh Nopember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.12962/j25481479.v7i4.14898

Abstract

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 () in the injection slot. The variation of  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  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/Cdcurve 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. 
Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale James Julian; Waridho Iskandar; Fitri Wahyuni
International Journal of Marine Engineering Innovation and Research Vol 8, No 2 (2023)
Publisher : Institut Teknologi Sepuluh Nopember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.12962/j25481479.v8i2.16432

Abstract

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.
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 : Institut Teknologi Sepuluh Nopember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.12962/j25481479.v8i4.18891

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 Armansyah Armansyah Bunga, Nely Toding Ferdyanto Ferdyanto Fitri Wahyuni James Julian Mirza Fauzan Lukiano Rifqi Ramadhani