Dewantara, Abi Surya (2023) Studi Eksperimen Pengaruh Penggunaan Wingtip Tipe Blended Winglet Dengan Cant Angle 15°, 30°, Dan 45° Terhadap Performa Aerodinamis Pada UAV Fixed Wing Arnayadirga Bayucaraka ITS. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
UAV atau pesawat tanpa awak memiliki berbagai macam kegunaan salah satunya yaitu untuk melakukan pemetaan demi kebutuhan pembangunan. Dalam upaya untuk memajukan dunia UAV di Indonesia, pemerintah melaksanakan Kontes Robot Terbang Indonesia (KRTI). Salah satu kategori yang diperlombakan adalah divisi fixed wing. Divisi ini memiliki misi untuk mengirimkan payload menuju suatu target pada jarak yang cukup jauh serta memetakan jalur yang dilewati selama penerbangan. Pesawat yang diperlombakan pada divisi ini harus didesain agar dapat membawa beban yang berat untuk waktu penerbangan yang lama. Dalam penelitian ini, dilakukan analisa berbasis eksperimen pada pengaruh pemasangan blended winglet dengan variasi cant angle terhadap performa aerodinamis dan persebaran tekanan pada sayap UAV fixed wing Arnayadirga Bayucaraka ITS. Penelitian dilakukan menggunakan wind tunnel Departemen Teknik Mesin ITS pada kecepatan freestream 9,35 m/s. Model sayap yang digunakan memiliki konfigurasi tapered dan menggunakan airfoil NACA 2312. Variasi terdapat pada jenis wingtip yang digunakan yaitu fillet wingtip dan blended winglet dengan cant angle 15°, 30°, dan 45°. Berdasarkan penelitian yang dilakukan, penggunaan blended winglet pada konfigurasi sayap UAV Fixed Wing Bayucaraka ITS dapat meningkatkan perbedaan tekanan antara permukaan atas dan permukaan bawah ujung sayap. Hal ini mengindikasikan bahwa efek wingtip vortex yang terjadi di sekitar ujung sayap berkurang. Namun, pengaruh tersebut tidak dapat dialami sayap saat setelah terjadi kondisi stall dimana aliran udara yang dilewati oleh sayap bersifat turbulen. Selain itu, didapatkan bahwa penambahan blended winglet dengan cant angle bervariasi dapat mempengaruhi efisiensi aerodinamika dari sayap pesawat UAV Fixed Wing Bayucaraka ITS. Dengan melihat perubahan nilai CL, CD, dan CL/CD rata-rata, didapatkan bahwa penambahan blended winglet dengan cant angle 15° dapat meningkatkan efisiensi aerodinamika dari sayap UAV Fixed Wing Bayucaraka ITS. Namun, terdapat penurunan efisiensi aerodinamika pada penambahan blended winglet dengan cant angle 30° dan 45°.
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UAVs or unmanned aircraft have various uses, one of which is to carry out mapping for development needs. In an effort to advance UAV technology in Indonesia, the government is implementing the Indonesian Flying Robot Contest (KRTI). One of the categories contested is the fixed wing division. This division has a mission to send a payload to a target at a considerable distance and map the path traversed during flight. The aircraft that are contested in this division must be designed to be able to carry a heavy load for a long flight time. In this study, an experimental-based analysis will be carried out on the effect of installing blended winglets with cant angle variations on aerodynamic performance and pressure distribution on the fixed wing UAV Arnayadirga Bayucaraka ITS. The research was conducted using a wind tunnel from the Department of Mechanical Engineering ITS at a freestream speed of 10 m/s. The wing model used has a tapered configuration and with NACA 2312 airfoil. There are variations in the type of wingtip used, namely fillet wingtip and blended winglet with cant angles of 15°, 30°, and 45°. Based on the conducted research, the utilization of blended winglets in the wing configuration of the Bayucaraka ITS Fixed Wing UAV can enhance the pressure difference between the upper and lower surfaces of the wingtip. This indicates a reduction in the wingtip vortex effect that occurs around the wingtip. However, this influence cannot be experienced by the wing after a stall condition occurs, where the airflow passing over the wing becomes turbulent. Additionally, it was found that the addition of blended winglets with varying cant angles can affect the aerodynamic efficiency of the Bayucaraka ITS Fixed Wing UAV wing. By examining the changes in the average values of CL, CD, and CL/CD, it was determined that the addition of blended winglets with a cant angle of 15° can enhance the aerodynamic efficiency of the Bayucaraka ITS Fixed Wing UAV wing. However, there is a decrease in aerodynamic efficiency when blended winglets with cant angles of 30° and 45° are added.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Aerodinamika, Blended Winglet, Efisiensi, UAV, Aerodynamic, Blended Winglet, Eficiency |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic. T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL777 Details and parts of models (Including propellers) |
| Divisions: | Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Abi Surya Dewantara |
| Date Deposited: | 29 Aug 2023 02:00 |
| Last Modified: | 29 Aug 2023 02:00 |
| URI: | http://repository.its.ac.id/id/eprint/102852 |
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