Usman, Muhammad (2024) Analisa Pengaruh Airfoil NACA 2412 dengan Variasi Taper Ratio dan Sudut Serang terhadap Cl dan Cd pada Sayap UAV dengan Metode Computational Fluid Dynamics. Undergraduate thesis, Universitas 17 Agustus 1945 Surabaya.
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Abstract
Peforma aerodinamis yang diinginkan dalam mendesain UAV sebisa mungkin memiliki CL yang tinggi dan CD yang kecil, Oleh karena itu, diperlukan desain pesawat yang memiliki perbandingan CL dan CD yang optimal. Peningkatan performa airfoil sayap UAV dapat dilakukan dengan berbagai cara, salah satunya yaitu mengubah taper ratio pada sayap pesawat tanpa awak dengan tujuan mencari nilai taper ratio yang dapat menghasilkan performa tertinggi. Taper rasio merupakan perbandingan antara tip chord (Ct) dengan root chord (Cr). semakin tirus bentuk sayap, maka taper ratio semakin rendah. Pada penelitian ini dilakukan simulasi numerik CFD mengguanakan software ansys, untuk mengetahui performa aerodinamika (L/D) sayap airfoil NACA 2412 dengan variasi tapper ratio 1: 0,75: 0,5. Performa aerodinamika terbaik berdasarkan nilai L/D mampu dicapai pada ketiga sayap taper ratio adalah konfigurasi sayap TR 1 dengan sudut serang 5 derajat menghasilkan nilai L/D = 6,33
| Item Type: | Thesis (Undergraduate) |
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| Uncontrolled Keywords: | Koefisien Angkat, Koefisien Hambat, Aerodinamis, NACA 2412, CFD |
| Subjects: | Q Science > QC Physics T Technology > TJ Mechanical engineering and machinery |
| Divisions: | Fakultas Teknik > Program Studi Teknik Mesin |
| Depositing User: | 1422000080 Muhammad Usman |
| Date Deposited: | 18 Jun 2026 10:18 |
| Last Modified: | 18 Jun 2026 10:18 |
| URI: | http://repository.untag-sby.ac.id/id/eprint/32581 |
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