Studi Numerik Pengaruh Penambahan Semicircular Bump Terhadap Karakteristik Aerodinamika Dari Airfoil NACA 0012

Baraja, Muhammad Helmi (2024) Studi Numerik Pengaruh Penambahan Semicircular Bump Terhadap Karakteristik Aerodinamika Dari Airfoil NACA 0012. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Airfoil merupakan sebuah struktur yang didesain untuk memanipulasi aliran fluida agar timbul reaksi tertentu. Airfoil diharapkan mampu memanipulasi fluida sehingga system dapat bergerak dengan mudah dan memiliki gaya hambat (drag force) yang rendah. Gaya drag selain menghambat system bekerja, juga dapat menurunkan gaya lift yang dapat menimbulkan separasi dan akan terjadi stall dalam keadaan angle of attack tertentu. Untuk mencegah hal ini maka aliran melintas harus mempunyai momentum yang kuat sehingga dapat bertahan mengikuti bentuk airfoil, aliran turbulen cenderung menunda separasi karena memiliki momentum yang kuat. Sehingga penelitian ini memiliki tujuan untuk mengubah aliran menjadi turbulen pada saat melewati area favorable pressure gradient. Penelitian ini dilakukan dengan metode numerik. Benda uji adalah airfoil NACA 0012 yang diberi obstacle berupa bump pada area favorable pressure gradient. Variasi dilakukan dalam beberapa letak bump (25%, 50%, dan 75% sebelum ketebalan maksimal airfoil) dan angle of attack (0°,8°, dan 12°). Penelitian ini dilakukan dengan Reynold number 6×106 dan sreamline velocity 52 m/s. geometri airfoil adalah 250 mm chord dan ukuran bump sebesar 3 mm. Analisa dilakukan dalam software ANSYS Fluent. Dari penelitian yang dilakukan didapatkan hasil bahwa dengan melakukan penambahan bump pada airfoil maka bubble separation dapat timbul, bubble paling efektif berada pada peletakan bump paling akhir yaitu b/c=0,225 diikuti b/c=0,15 dan b/c=0,075. Namun timbulnya bubble pada airfoil belum mampu meningkatkan nilai dari koefisien lift airfoil bila dibandingkan dengan airfoil tanpa bump, nilai lift yang paling mendekati nilai dari lift pada airfoil polos yaitu b/c=0,225 diikuti b/c=0,15 dan b/c=0,075. Dan nilai koefisien drag pada airfoil dengan bump masih llebih tinggi dari airfoil tanpa bump, nilai koefisien drag yang paling mendekati ada pada bump b/c=0,225 diikuti b/c=0,15 dan b/c=0,075.
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Airfoil is a structure designed to manipulate fluid flow so that certain reactions occur. The airfoil is expected to be able to manipulate fluid so that the system can move easily and has low drag force. Apart from preventing the system from working, the drag force can also reduce the lift force which can cause separation and stall at certain angles of attack. To prevent this, the passing flow must have strong momentum so that it can maintain following the shape of the airfoil. Turbulent flow tends to delay separation because it has strong momentum. So this research aims to change the flow to become turbulent at favorable pressure gradient area. This research was carried out using numerical methods. The test object is a NACA 0012 airfoil which is given an obstacle in the form of a bump in the favorable pressure gradient area. Variations were made in several bump locations (25%, 50%, and 75% before the maximum airfoil thickness) and angle of attack (0°, 8°, and 12°). This research was conducted with a Reynold number of 6×106 and a streamline velocity of 52 m/s. The airfoil geometry is 250 mm chord and size of the semicircular bump is 3 mm. Analysis was carried out in ANSYS Fluent software. From the research conducted, it was found that by adding a bump to the airfoil, bubble separation can arise, the most effective bubble is at the last bump placement, namely b/c=0.225 followed by b/c=0.15 and b/c=0.075. However, the onset of bubbles on the airfoil has not been able to increase the value of the airfoil lift coefficient when compared to the airfoil without bump, the value of the lift that is closest to the value of the lift on the plain airfoil is b/c=0.225 followed by b/c=0.15 and b/c=0.075. And the drag coefficient value on the airfoil with bump is still higher than the airfoil without bump, the closest drag coefficient value is on the bump b/c=0.225 followed by b/c=0.15 and b/c=0.075.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Airfoil NACA 0012, bump, turbulen, studi numerik, turbulent, numerical study
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL507.G77 Vortex generators.
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Muhammad Helmi Baraja
Date Deposited:	27 Aug 2024 01:30
Last Modified:	27 Aug 2024 01:30
URI:	http://repository.its.ac.id/id/eprint/114233

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