Al-Ghazali, Darussalam Fattah (2025) Studi Numerik Karakteristik Aliran Tiga Dimensi Airfoil NACA 4412 dengan Variasi Backward Swept Angle (Λ) 0°, 10°, 20°, 30° dan Angle of Attack (α) 0°, 8°, 16. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Pesawat tanpa awak (UAV) semakin banyak digunakan untuk berbagai kebutuhan seperti pemantauan wilayah, pengiriman logistik, hingga misi militer. Namun, performa aerodinamikanya masih menghadapi tantangan signifikan, terutama terkait gaya hambat dan efisiensi manuver. Salah satu pendekatan desain yang digunakan untuk meningkatkan efisiensi aerodinamika adalah penerapan sudut swept pada sayap. Penelitian ini fokus pada analisis numerik tiga dimensi untuk mengetahui pengaruh backward swept angle di sayap Airfoil NACA 4412 terhadap pengaruh angle of attack Penelitian ini menggunakan metode simulasi numerik tiga dimensi dengan aliran steady, viscous, dan incompressible. Geometri sayap didesain menggunakan SolidWorks 2022, meshing dilakukan menggunakan ICEM CFD 2025 R1 Student, dan simulasi dilakukan pada ANSYS Fluent 2025 R1 Student. Model turbulensi yang digunakan adalah k-omega SST. Variasi sudut swept angle yang dianalisis adalah 0°, 10°, 20°, dan 30°, serta variasi sudut serang sebesar 0°, 8°, dan 16°, dengan kecepatan aliran 20,833 m/s dan bilangan Reynolds 3,61 × 10⁵. Analisis meliputi distribusi pressure coefficient (Cp), koefisien gaya angkat (Cl), gaya hambat (Cd), serta rasio Cl/Cd, kontur kecepatan, streamline, dan vortex pada tip wing.Hasil penelitian menunjukkan bahwa peningkatan swept angle menyebabkan penurunan gradien tekanan (Cp) di upper surface, terutama di tip, yang mengakibatkan penurunan gaya angkat lokal. Namun, rasio lift-to-drag (Cl/Cd) meningkat secara signifikan pada α = 0° dan α = 8°, dengan nilai tertinggi 19,76 pada Λ = 30° dan α = 8° dibandingkan α = 16°, menunjukkan efisiensi aerodinamika tertinggi. Sebaliknya, pada α = 16°, terjadi penurunan nilai performa Cl/Cd pada Λ = 30° dengan nilai 7,05 akibat fenomena separasi aliran dan menunjukan indikasi
stall.
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Unmanned Aerial Vehicles (UAVs) are increasingly being used for various purposes such as surveillance, logistics delivery, and military missions. However, their aerodynamic performance still faces significant challenges, particularly related to drag and manuver ability efficiency. One of the design approaches used to improve aerodynamic efficiency is the application of swept angles on the wings. This study focuses on a three-dimensional numerical analysis to examine the effect of backward swept angles on the NACA 4412 airfoil in relation to the angle of attack. This research uses a three-dimensional numerical simulation method with steady, viscous, and incompressible flow. The wing geometry was designed using SolidWorks 2022, meshing was carried out using ICEM CFD 2025 R1 Student, and simulations were conducted using ANSYS Fluent 2025 R1 Student. The turbulence model employed is k-omega SST. The variations of swept angle analyzed are 0°, 10°, 20°, and 30°, while the angle of attack variations are 0°, 8°, and 16°, with an inflow velocity of 20,833 m/s and a Reynolds number of approximately 3,61 × 10⁵. The analysis includes the distribution of pressure coefficient (Cp), lift coefficient (Cl), drag coefficient (Cd), as well as the Cl/Cd ratio, velocity contours, streamlines, and vortex patterns at the wingtip. The results of the study show that an increase in swept angle leads to a decrease in the pressure gradient (Cp) on the upper surface, particularly at the tip, resulting in a reduction in local lift. However, the lift-to-drag ratio (Cl/Cd) increases significantly at α = 0° and α = 8°, with the highest value of 19,76 observed at Λ = 30° and α = 8°, indicating the highest aerodynamic efficiency. Conversely, at α = 16°, efficiency decreases with Cl/Cd ratio of only 7,05 at Λ = 30° due to flow separation phenomena and indications of stall.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Airfoil NACA 4412, Lift-to-drag, Swept Angle, Tip-vortex, Stall, Separasi |
| Subjects: | U Military Science > U Military Science (General) U Military Science > U Military Science (General) > UG Military Engineering > UG1242.D7 Unmanned aerial vehicles. Drone aircraft U Military Science > U Military Science (General) > UG Military Engineering |
| Divisions: | Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Darussalam Fattah Al-ghazali |
| Date Deposited: | 31 Jul 2025 04:40 |
| Last Modified: | 31 Jul 2025 04:40 |
| URI: | http://repository.its.ac.id/id/eprint/124071 |
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