The Effect of Plasma Actuator Placement on Drag Coefficient Reduction of Ahmed Body as an Aerodynamic Model

Julian, James W.; Harinaldi, Harinaldi; Budiarso, Budiarso; Difitro, Revan; Stefan, Parker

doi:10.14716/ijtech.v7i2.2994

Cited by 17 publications

(10 citation statements)

References 1 publication

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“…Penelitian terdahulu juga dilakukan oleh Kang Pyo Cho, Seung Hwan Jeong, Dany Perwita Sari [10] yang membahas pengaruh gaya Lift terhadap sudut serang Pesawat terbang NACA 4 Digit Seri yang berbeda juga. Penelitian lain yang serupa dilakukan secara experimental pada wind tunnel dengan variasi kecepatan input yang dilakukan oleh James Julian, Harinaldi, Budiarso, Revan Difitro, Parker Stefan [9] .…”

Section: Pendahuluanunclassified

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Hidayat

Nofendri

2019

Prosid Sem Nas Teknoka

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Dunia Kedirgantaraan di Indonesia yang semakin lesu, butuh Peneliti-peneliti bertalenta di bidang Aerodinamika agar bisa mengangkat kembali nama baik dan harga diri Bangsa. Penelitian saya kali ini bertemakan studi bidang aerodinamika dari potongan melintang sayap pesawat terbang type Airfoil NACA 0013 dengan mencari sudut serang yang tepat untuk Take Off. Tujuan Penelitian ini adalah untuk menentukan sudut serang terbaik dari Pesawat saat Take Off. Metode yang saya gunakan dengan penerapan Simulasi CFD menggunakan Software ANSYS-Fluent versi 14.5 dengan Workbench. Hasil yang di dapat dari penelitian ini akan ditabulasikan dalam tabel dan grafik hubungan antara Gaya Lift terhadap Sudut Serang. Dengan mengambil variabel sudut serang sebanyak 9 variabel yaitu 0o, 3o, 6o, 9o, 12o, 15o, 18o, 21o, dan 24o. Dari hasil Simulasi didapat Sudut Serang terbaik untuk tipe NACA 0013 adalah 21o dengan harga Gaya Lift sebesar 61,650 N.

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Section: Pendahuluanunclassified

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Hidayat

Nofendri

2019

Prosid Sem Nas Teknoka

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“…Fluid flow separation can make Cd airfoil increase [3] [4]. Further, the separation can also cause the airfoil to undergo a very drastic decrease in Cl which is called stall [5].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics Improvement of NACA 0015 by Using Co-Flow Jet

Julian

Iskandar²,

Wahyuni³

2022

IJMEIR

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⎯ 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.

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“…Airfoil is a cross-sectional shape commonly found on aircraft wings, wind turbine blades, helicopter blades and others. When the airfoil moves with an extreme AoA (angle of attack), the fluid flow cannot follow the shape of the airfoil (Megawanto et al, 2018;Julian, Difitro and Stefan, 2016). The separation of fluid flow on the upper side of the airfoil can cause an increase in the drag force of the airfoil (Harinaldi, Budiarso and Julian, 2016).…”

Section: Introductionmentioning

confidence: 99%

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

Julian

Iskandar²,

Wahyuni³

et al. 2022

ASIIMETRIK

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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.

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The Effect of Plasma Actuator Placement on Drag Coefficient Reduction of Ahmed Body as an Aerodynamic Model

Cited by 17 publications

References 1 publication

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Pengaruh Gaya Lift Terhadap Sudut Serang Airfoil Naca 0013 dengan Ansys Fluent

Aerodynamics Improvement of NACA 0015 by Using Co-Flow Jet

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

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