Studi Numerik Karakteristik Aliran Tiga Dimensi Melewati Airfoil NACA 4412 dengan Swept Angle(Λ) 0O, 15O, dan 30O pada Low Wing Arrangement

Hartanto, Wahyu Indra Dwi (2019) Studi Numerik Karakteristik Aliran Tiga Dimensi Melewati Airfoil NACA 4412 dengan Swept Angle(Λ) 0O, 15O, dan 30O pada Low Wing Arrangement. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Sayap merupakan komponen terpenting yang mempengaruhi performa pesawat terbang. Sayap disusun oleh airfoil yang dapat menimbulkan gaya angkat pada pesawat terbang. Gaya angkat terjadi karena adanya perbedaan tekanan pada bagian bawah dan atas airfoil. Penelitian untuk mendapatkan performa aerodinamika yang lebih baik pada pesawat telah banyak dilakukan. Salah satunya yaitu penempatan posisi sayap pesawat pada fuselage (wing arrangement) dan merubah sudut kemiringan rentang airfoil (swept angle). Hal ini sering terlihat pada hampir semua pesawat komersial seperti BOEING 747 dan AIRBUS A330. Metode yang akan digunakan pada studi ini adalah simulasi numerik tiga dimensi dengan menggunakan software Solidworks, Gambit 16.2 dan Fluent 18.2. Benda uji berupa airfoil NACA 4412 dengan panjang chord 100 mm dan menggunakan konfigurasi sayap rendah rendah (low-wing arrangement). Aspect ratio (AR) sebesar 5, sudut serang dijaga konstan (0o) dan variasi berupa unswept Λ = 0° serta backward swept angle Λ = 15° dan Λ = 30°. Turbulence model yang digunakan adalah k-ω SST. Aliran fluida merupakan udara yang mengalir dengan dengan bilangan Reynolds (Re) = 1 x 106 pada kondisi steady. Dari penelitian ini didapatkan performa aerodinamika dan fenomena aliran di sekitar airfoil. Performa terbaik berdasarkan rasio CL/CD terdapat pada airfoil dengan sudut swept 30° dengan nilai 18.2. Penambahan swept angle mengakibatkan vortex di sekitar fuselage mengecil. Penambahan swept angle juga mampu menurunkan tekanan di daerah leading edge, namun tekanan pada upper surface meningkat dan pada lower surface turun. Hal tersebut yang menyebabkan nilai C¬L dan CD turun walau performanya semakin meningkat seiring penambahan swept angle.
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The wings are the most important component that affects aircraft performance. They have basic shape of airfoil which produce lift force on an airplane. Lift force occured because of the difference in pressure on the bottom and on the top surfaces of the airfoil. Many researches to obtain better aerodynamic performance on airplane have been done. One of them is the placement of the wing position on the fuselage (wing arrangement) and changing the swept angles. This is often seen in almost all commercial aircraft such as the BOEING 747 and AIRBUS A330. The method that used in this study is a three-dimensional numerical simulation using softwares Solidworks, Gambit 16.2 and Fluent 18.2 . The test model is NACA 4412 airfoil with 100 mm chord length for low-wing arrangement. The aspect ratio (AR=S/C) is 5, the angle of attack is kept constant (0o) and the variation are unswept Λ = 0° and backward swept angle Λ = 15° and Λ = 30°. The turbulence model is k-ω SST. The fluid flow is air with Reynolds number (Re) = 1 x 106 in steady state. The results of this research are the aerodynamic performance and phenomenon of flow around the airfoil. The best performance based on the CL/CD ratio is on airfoil with swept angle of 30° with a value of 18.2. The addition of swept angle reduces vortex around the fuselage. The addition of swept angle is also able to reduces the pressure at the leading edge area, but the pressure on the upper surface increases and on the lower surface drops. This causes the values of CL and CD also drop, although the performance (CL/ CD) increases with the addition of the swept angle.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	airfoil, NACA 4412, backward swept angle, low-wing arrangement
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions:	Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Wahyu Indra Dwi Hartanto
Date Deposited:	21 Jul 2026 08:56
Last Modified:	21 Jul 2026 08:56
URI:	http://repository.its.ac.id/id/eprint/66537

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