Ridha, Rasyid (2017) Studi Numerik Karakteristik Aliran 3 Dimensi di Sekitar Airfoil NACA 0012 dengan Backward Swept Angle 0°, 15°, dan 30°. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Airfoil merupakan suatu struktur aerodinamika yang banyak digunakan baik pada sayap pesawat maupun mesin - mesin fluida seperti pompa, kompresor, dan turbin. Airfoil pada sayap pesawat digunakan untuk mengangkat badan pesawat. Perbedaan tekanan antara bagian atas dan bawah airfoil menyebabkan pesawat mendapat gaya angkat. Peningkatan performa airfoil dapat dilakukan dengan berbagai cara, salah satunya yaitu mengubah sudut kemiringan pada rentangan airfoil (swept angle). Hal ini sering terlihat pada hampir semua jenis pesawat terbang komersial seperti BOEING 777 dan AIRBUS 380. Metode yang akan digunakan pada studi ini adalah simulasi numerik tiga dimensi dengan menggunakan software Gambit dan Fluent 2.6. Benda uji berupa airfoil NACA 0012 dengan panjang chord 100 mm, aspect ratio (AR) sebesar 5, sudut serang 8° dan 15°, dan variasi backward swept angle Λ = 0°(unswept), 15° dan 30°. Aliran fluida merupakan udara yang mengalir dengan dengan bilangan Reynolds (Re) = 1 x 105 pada kondisi steady. Dari penelitian ini didapatkan performa aerodinamika dan fenomena aliran di sekitar airfoil. Pada sudut serang 8°, performa terbaik berdasarkan rasio CL/CD terdapat pada airfoil dengan sudut swept 15°, sedangkan swept angle 30° menjadi konfigurasi airfoil terbaik pada sudut serang 15°. Selain itu, penambahan sudut swept mengakibatkan vortex di sekitar wall body junction mengecil tetapi meningkatkan tip vortex. ==============================================================Airfoil is an aerodynamic structure which generally utilize on an aircraft wing as well as turbomachinery such as pump, compressor, and turbine. On an aircraft, airfoil act as a wing to lift the aircraft fuselage. Pressure different between upper and lower surface of an airfoil generate a lift force to the aircraft. Airfoil performance could be improved with many ways, include changing it swept angle. It can be seen at almost all commercial aircraft such as BOEING 777 and AIRBUS 380. Method used is three-dimensional numerical simulation using Gambit and Fluent 2.6. Test object is NACA 0012 airfoil which has chord length of 100 mm, aspect ratio of 5, angle of attack of 8° and 15°, as well as backward swept angle (Λ) variation of 0°(unswept), 15° and 30°. Fluid which flow in this test is air with Reynolds Number (Re) of 1 x 105 in steady condition. Result gained from this study are aerodynamic performance and flow phenomenon around airfoil. At angle of attack of 8°, the best performance according to CL/CD ratio is airfoil with 15° swept angle while 30° swept angle become the best configuration at 15° angle of attack. Furthermore, increasing swept angle caused reduction of vortex around wall body junction while increasing tip vortex in contrast.
| Item Type: | Thesis (Undergraduate) |
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| Uncontrolled Keywords: | Airfoil; NACA 0012; Sudut Swept; Tip Vortex |
| Subjects: | T Technology > TJ Mechanical engineering and machinery |
| Divisions: | Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Rasyid Ridha . |
| Date Deposited: | 07 Sep 2017 08:16 |
| Last Modified: | 05 Mar 2019 06:29 |
| URI: | https://repository.its.ac.id/id/eprint/42846 |
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