Amri, Nuri Deza Auliya (2019) Analisa Karakteristik Aliran Pengaruh Pemberian Gurney Flap Terhadap Koefisien Lift dan Rasio Lift To Drag Dengan Variasi Panjang Flap 1%, 2%, Dan 3% Dari Panjang Chord Pada Model Sayap Airfoil Naca 2415. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Sejak lahirnya prototipe pesawat terbang oleh Wright bersaudara pada tahun 1903, industri penerbangan mengalami perkembangan yang pesat khususnya dalam perkembangan model pesawat. Pada saat ini perkembangan model sayap memungkinkan untuk mendapatkan variasi nilai lift dan drag sesuai dengan kebutuhan pesawat. Salah satu perkembangan model sayap ini adalah dengan penambahan Gurney flap. Dalam beberapa penelitian, penambahan Gurney flap menunjukkan terjadinya peningkatan lift, rasio lift to drag pada model airfoil/sayap dengan penambahan flap ini. Maka dari itu, penelitian ini dimaksudkan untuk menganalisa peningkatan lift coefficient (CL), lift to drag coefficient (CL/CD), serta fenomena separasi pada model sayap dengan basis airfoil NACA 2415. Pada studi ini, metode yang digunakan adalah simulasi numerik 3 dimensi dengan menggunakan perangkat lunak Gambit dan Ansys Fluent. Benda uji berupa sayap dengan basis airfoil NACA 2415 dengan panjang chord 180 mm, aspect ratio (AR) = 1. Sayap diletakan tegak lurus dinding dengan kondisi aliran melewati sayap di dalam wind tunnel. Penambahan Gurney flap diberikan dengan variasi panjang (t) = 1%, 2%, dan 3% panjang chord serta variasi angle of attack (α) = 0o, 3o, dan 6o. Simulasi ini menggunakan turbulence model k-ω SST. Aliran pada simulasi ini dikondisikan steady dan incompressible dengan bilangan Reynolds (Re) = 1 x 105. Berdasarkan hasil penelitian ini, pemberian Gurney flap terbukti memberikan pengaruh terhadap peningkatan nilai CL, dan CL/CD. Dari analisa performa aerodinamika pada tiap variasi model, koefisien CL paling tinggi (CL = 0.6228, α = 6o) didapatkan pada model Gurney flap dengan panjang 3% chord, sedangkan koefisien CL/CD paling tinggi (CL/CD = 9.58, α = 3o) didapatkan pada model Gurney flap dengan panjang 3% chord. Pada model sayap dengan panjang Gurney flap 1% chord, nilai CL/CD tidak mengalami penurunan terhadap kenaikan α. Dari analisa karakteristik aliran berupa kontur tekanan, penambahan Gurney flap mengakibatkan peningkatan tekanan pada daerah lower surface di depan flap. Dari analisa karakteristik aliran pada daerah trailing edge, separasi mengalami penudaan pada upper surface akibat penambahan Gurney flap akibat tabrakan aliran dengan flap.
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Since the first invention aircraft prototype by the Wright brothers in 1903, the aviation industry has experienced rapid development especially in aircraft modelling. At this time, the development of the wing model gives possible variations in the lift and drag values according to the needs. One of the its development is the addition of Gurney flap. In several studies, the addition of Gurney flap attachment showed an increasing in lift and the ratio of lift to drag on the airfoil / wing model. Therefore, the purpose of this to analyze the increase in lift coefficient (CL), lift to drag coefficient (CL / CD), and the phenomenon of separation around the NACA 2415 airfoil-based wing model. A 3-dimensional numerical method used in this study with the using of Gambit and Ansys Fluent software. The specimen is a NACA 2415 airfoil-based wing model with chord length of 180 mm, aspect ratio (AR) = 1. The wing is attached perpendicular to the wall with the condition of the flow passing through the wing inside the wind tunnel. Gurney flap attachment is given with variations in length (h) = 1%, 2%, and 3% of chord length and variations in angle of attack (α) = 0o, 3o, and 6o. Turbulence model of k-ω SST is used in this simulation. In this simulation, the flow model is steady and incompressible with the Reynolds number (Re) = 1 x 105. Based on the simulation results, the Gurney flap attachmenthad been proved to increase the CL, and CL / CD values. From the analysis of aerodynamic performance, the highest CL (CL = 0.6228, α = 6o) was obtained at the Gurney flap model with a length of 3% chord, while the highest CL / CD (CL / CD = 9.58, α = 3o ) obtained at the Gurney flap model with a length of 3% chord. At the Gurney flap model with a length of 1% chord, the value of CL / CD did not drop due to increasing of α. From the analysis of flow characteristics in the form of pressure contour, the Gurney flap attachment increases pressure on the lower surface area at front of the flapl. From the analysis of flow characteristics on the trailing edge area, the upper surface separation goes backward due to collisions with the flap.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Airfoil, Gurney flap, Lift , NACA 2415, Rasio Lift to Drag , Separasi |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic. |
| Divisions: | Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Nuri Deza Auliya Amri |
| Date Deposited: | 21 Jul 2026 04:26 |
| Last Modified: | 21 Jul 2026 04:26 |
| URI: | http://repository.its.ac.id/id/eprint/67581 |
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