Analisa Aerodinamika Airfoil Naca 0021 Dengan Ansys Fluent

Hidayat, M Fajri

doi:10.52447/jktm.v1i1.332

Cited by 7 publications

(6 citation statements)

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“…Dalam penelitian ini terowongan angin, USAF DATCOM dan hasil CFD, semuanya menunjukkan tren yang serupa. (Hidayat, 2016) melakukan penelitian dengan judul "Analisa Aerodinamika Airfoil NACA 0021 dengan ANSYS fluent". Penelitian ini melakukan analisis performa aerodinamika suatu penampang airfoil untuk menentukan gaya angkat maksimum yang terjadi serta gaya-gaya yang bekerja pada penampang airfoil seperti gaya drag dan gaya lift.…”

Section: Pendahuluanunclassified

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Dede Dahendi,

Yudhono,

Armelia Erissonia

2023

teknika

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The purpose of this research is to make a very small unmanned aircraft as a teaching aid in aerospace engineering workshops, because of its very small size, this type of unmanned aircraft is abbreviated as Micro Air Vehicle, this MAV is only operated at low Reynolds numbers. MAV development research for smaller sizes continues to be carried out such as the Micro Glider. In this study, the author uses the Computational Fluid Dynamic method and the software used ANSYS Fluent and compares the existing DATCOM data, the author simulates the 4 types of airfoils into a wing object. The results of this study can be seen that based on the average deviation diff value that has been obtained in a population to determine the error from the comparison of the reference airfoil lift coefficient and its FFP by comparing the two methods, namely the IISHI airfoil reference geometry is 6.22% while the FFP is is 11.25% and the SD 7037 airfoil reference geometry is 3.71% while the FFP is 2.11%. Then for the comparison of the maximum lift to drag ratio values, it is obtained that the airfoil reference geometry (SD 7037) has a value of = 9.96 while the airfoil reference geometry (IISHI) has a value of = 8.81. In the Folded Flat Plate airfoil geometry (SD 7037) it has a value of = 7.61 while the Folded Flat Plate airfoil (IISHI) has a value of = 7.37. Then for the visualization of fluid flow can be obtained, namely the results of visualization of fluid flow in several parts of the angle of view / plane of the wing geometry when the AoA is high, namely the root plane to the half wing plane. early, while the geometry of SD 7037 (airfoil reference) is not easy to occur early turbulence flow. Second, that in general the fluid flow pattern seen in the FFP airfoil geometry (FFP IISHI) has the most dominant turbulence flow pattern (very much/large) while the FFP airfoil geometry (FFP SD 7037) has very little/small turbulence flow pattern..

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Section: Pendahuluanunclassified

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Dede Dahendi,

Yudhono,

Armelia Erissonia

2023

teknika

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“…Airfoil memiliki banyak jenis, beberapa yang terkemuka adalah Selig, Gottingen, FX Wortmann, dan NACA airfoil [3] [4]. NACA airfoil adalah tipe geometri airfoil yang dikembangkan oleh National Advisory Committee for Aeronautics (NACA) dengan memperhitungkan pengaruh kelengkungan surface airfoil dan penyebaran ketebalan (thickness) serta pemakaian nilai bilangan Reynold tertentu dalam pengujiannya [5]. NACA airfoil memiliki Cl dan Cd rendah dibandingkan jenis airfoil yang lain sehingga cocok untuk pesawat yang membutuhkan kecepatan tinggi dan beban yang ringan [6].…”

Section: Pendahuluanunclassified

“…NACA airfoil memiliki Cl dan Cd rendah dibandingkan jenis airfoil yang lain sehingga cocok untuk pesawat yang membutuhkan kecepatan tinggi dan beban yang ringan [6]. Oleh karena itu NACA banyak digunakan pada Unmanned Aerial Vehicle (UAV) [5].…”

Section: Pendahuluanunclassified

Comparison Lift and Drag of Airfoil NACA 1408 Standard and Modification Using Computational Fluid Dynamic

Usin¹,

Fernanda²,

Karudin³

et al. 2022

motivection

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An airfoil is a geometry shape of an aircraft wing designed to produce high lift force and low drag forces. Study on the air flow and pressure around of the airfoil was important step to analysis lift force and drag force. Factor affecting the lift force and drag force airfoil are the geometry and dimensions of the airfoil. This study to discus about the modification airfoil NACA 1408 was performed by adding round tip in leading edge to obtain simulate air flow by varying the angle of attack. The result showed that coefficient of lift (Cl) and coefficient of drag (Cd) was calculated from the simulations, data the highest Cl and Cd were 0.00277 and 0.00025 for the standard airfoil and for modification airfoil were 0.00343 and 0.00064. Based on the test result, the modified airfoil can produce better lift force than the standard shapes for test speed of 20 m/s. Airfoil merupakan bentuk geometri sayap pesawat terbang yang dirancang untuk menghasilkan lift force tinggi dan drag force rendah. Studi tentang aliran udara dan tekanan di sekitar airfoil adalah langkah penting untuk menganalisis lift force dan drag force. Faktor yang mempengaruhi lift force dan drag force airfoil adalah geometri dan dimensi airfoil tersebut. Penelitian ini membahas tentang modifikasi dilakukan pada airfoil NACA 1408 dengan menambahkan ujung bulat pada leading edge dan mendapatkan simulasi aliran udara dengan memvariasikan angle of attack. Hasil penelitian menunjukkan bahwa coefficient of lift dan coefficient of drag dihitung dari simulasi, data coefficient of lift dan coefficient of drag tertinggi adalah 0.00277 dan 0.00025 untuk airfoil standar dan untuk airfoil modifikasi adalah 0.00343 dan 0.00064. Berdasarkan hasil pengujian, airfoil modifikasi dapat menghasilkan lift force lebih baik daripada bentuk standar untuk kecepatan uji 20 m/s.

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“…The NACA airfoil represents a geometric configuration that, when subjected to airflow, generates both lift and drag forces [6][7]. This phenomenon is fundamental in aviation, where the lift force surpasses the drag force, enabling flight [8] [9].…”

Section: Introductionmentioning

confidence: 99%

Wing Simulation Using Naca 2412 and 2415 Airfoils with Variations in Angle of Attack for Lift and Drag

Pane

2023

VANOS JMEE

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The geometry of an airfoil plays a critical role in shaping an aircraft's performance, especially during maneuvering. This study emphasizes the necessity of conducting a comprehensive geometric analysis to better understand the effects of airfoil design. In pursuit of optimizing airfoil performance, we conducted extensive tests on NACA 2412 and 2415 series airfoil geometries using the ANSYS Fluent software. The tests employed Aluminum Alloy 1067 material and a wind speed of 300 m/s, encompassing a range of angle of attack variations from 0 to 180 degrees. The simulation results provided valuable insights into the velocity and pressure distributions surrounding the airfoil. Of particular interest, at an angle of 15 degrees, the NACA 2412 airfoil exhibited a maximum drag force of 69.670 N and a maximum lift force of 550.300 N. The corresponding drag and lift coefficients were 0,1516378 N and 1,1977364 N. For the NACA 2415 airfoil, the maximum drag and lift forces were 71.470 N and 564.500 N, respectively, with corresponding drag and lift coefficients of 0,1541963 N and 1,2179072 N.

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Analisa Aerodinamika Airfoil Naca 0021 Dengan Ansys Fluent

Cited by 7 publications

References 0 publications

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Comparison Lift and Drag of Airfoil NACA 1408 Standard and Modification Using Computational Fluid Dynamic

Wing Simulation Using Naca 2412 and 2415 Airfoils with Variations in Angle of Attack for Lift and Drag

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