Irawan, Istihadi (2020) Studi Numerik Karakteristik Aliran Tiga Dimensi Melewati Airfoil Naca 4412 Dengan Backward Swept Angle (Λ) 0, 15 Dan 30 Pada High Wing Arrangement. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Sayap pesawat memiliki potongan melintang berbentuk airfoil. Bentuk inilah yang dapat membangkitkan gaya angkat (lift) pada pesawat akibat adanya perbedaan tekanan fluida yang mengalir pada sisi atas dan sisi bawah dari airfoil. Perbandingan antara koefisien gaya angkat dan gaya hambat (CL/CD) merupakan salah satu faktor yang menentukan perfomansi dari airfoil. Peningkatan performansi airfoil dapat dilakukan dengan berbagai cara, antara lain yaitu mengubah sudut kemiringan pada rentangan airfoil (swept angle) dan mengubah posisi pemasangan sayap (wing arrangement) terhadap fuselage. Metode yang digunakan pada studi ini adalah simulasi numerik tiga dimensi dengan menggunakan perangkat lunak Ansys Fluent. Benda uji berupa airfoil NACA 4412 dengan panjang chord 100 cm, aspect ratio (AR) sebesar 5 dan posisi penempatan sayap berada diatas terhadap fuselage (high wing arrangement). Swept angle (Λ) berupa backward dengan variasi sudut = 0°(unswept), 15° dan 30° serta sudut serang dijaga konstan (α = 0o). Simulasi ini menggunakan turbulence model k-ω SST. Fluida kerja merupakan udara yang mengalir dengan bilangan Reynolds (Re) = 1 x 106 pada kondisi steady. Hasil yang didapatkan dari penelitian ini, yaitu fenomena aliran di sekitar airfoil dan performa aerodinamika. Performa terbaik berdasarkan rasio CL/CD pada high wing arrangement terjadi pada airfoil dengan swept angle Λ = 30° dengan nilai 18.49. Penambahan swept angle mampu menurunkan tekanan di daerah leading edge, namun tekanan pada upper surface mengalami kenaikan. Hal tersebut yang menyebabkan nilai CL dan CD menurun meskipun performanya mengalami peningkatan seiring dengan bertambahnya swept angle.
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The cross section of aircraft wings are shaped as airfoil which generates lift on the aircraft due to the difference in fluid pressure flowing on the upper and lower surface of the airfoil. The comparison between lift force coefficient and drag force coefficient (CL/CD) is one of the factors that determine the performance of the airfoil. Improvements in airfoil performance can be done in various ways, such as changing the swept angle (Λ) and changing the wing arrangement relative to the fuselage. The method used in this study is a three-dimensional numerical simulation using the Ansys Fluent software. The specimen is an airfoil NACA 4412 with a chord length of 100 cm, aspect ratio (AR) of 5 and high wing arrangement. The swept angle (Λ) is backward with a variation of angle = 0° (unswept), 15° and 30 ° and the angle of attack is kept constant (α = 0o). This simulation uses k-ω SST turbulence model. The working fluid is the air flowing with Reynolds number (Re) = 1 x 106 with steady flow condition. The results obtained from this research are the phenomenon of flow around the airfoil and aerodynamic performance. The addition of swept angle reduces the pressure at the leading-edge region and increases the pressure on the upper surface. This causes CL and CD values to decrease even though the performance increase. The best performance based on CL/CD ratio occurs at swept angle Λ = 30 ° with the value of 18.49.
| Item Type: | Thesis (Other) |
|---|---|
| Additional Information: | RSM 629.134 32 Ira s-1 2020 |
| Uncontrolled Keywords: | airfoil, NACA 4412, backward swept angle, high wing arrangement. |
| Subjects: | T Technology > TJ Mechanical engineering and machinery > TJ935 Pipe--Fluid dynamics. Tubes--Fluid dynamics |
| Divisions: | Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Istihadi Irawan |
| Date Deposited: | 25 Apr 2024 10:35 |
| Last Modified: | 25 Apr 2024 10:35 |
| URI: | http://repository.its.ac.id/id/eprint/73673 |
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