Studi Numerik Pengaruh Vortex Generator Dekat Endwall Pada Pengendalian Aliran Sekunder Airfoil NASA LS-0417 Pada Posisi X/C = 0.45 Dan 0.55

Sean, Joshua Clarence (2022) Studi Numerik Pengaruh Vortex Generator Dekat Endwall Pada Pengendalian Aliran Sekunder Airfoil NASA LS-0417 Pada Posisi X/C = 0.45 Dan 0.55. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Desain dan konfigurasi sayap yang optimal memberikan pengaruh yang besar terhadap performansi, keamanan serta efisiensi dari suatu pesawat terbang. Memaksimalkan gaya
angkat (lift) serta meminimalkan gaya hambat (drag) pada kecepatan rendah dan sudut serang tinggi merupakan hal yang krusial. Peningkatan performansi dari sayap pesawat salah satunya dapat dilakukan dengan meningkatkan koefisien gaya angkat (CL) dan mengurangi koefisien gaya hambat (CD), sehingga ratio nilai (CL/CD) menjadi lebih besar.
Penelitian tugas akhir ini berwujud studi numerik terhadap analisa pengaruh penambahan rectangular vortex generator di dekat endwall terhadap karakteristik aliran yang melintasi airfoil NASA LS-0417. Adapun, variasi yang digunakan pada studi numerik ini berupa variasi posisi penempatan secara spanwise (4% dan 6%C), posisi penempatan secara chordwise (45%C dan 55%C), serta sudut serang 13o dengan sebuah perangat lunak CAD dan 3 perangkat lunak CFD berbasis komersial.
Dari hasil simulasi didapatkan bahwa, modifikasi airfoil dengan vortex generator di dekat endwall mampu mereduksi aliran sekunder yang berdampak terhadap peningkatan nilai CL/CD sebesar 27% dibandingkan plain airfoil pada posisi chordwise X/C : 0.55 dengan sudut serang 13o. Serta, penambahan vortex generator dinilai lebih efektif pada sudut serang tinggi, dikarenakan pada sudut serang 0o, efek reduksi aliran sekunder yang dihasilkan vortex generator dirasa minimal, dan menghasilkan drag yang lebih merugikan performansi dari sayap NASA LS-0417.
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Optimal wing design and configuration has a great influence on the performance, safety and efficiency of an aircraft. Maximizing lift and minimizing drag at low speeds and high angles of attack are crucial. One of the ways to improve the performance of aircraft wings is by increasing the lift coefficient (CL) and reducing the drag coefficient (CD), so that the ratio value (CL/CD) becomes greater.
This final project research, in the form of a numerical study is to analyze the effects of adding rectangular vortex generators near the endwall towards the flow characteristics across the NASA LS-0417 airfoil. The variations used in this numerical study are spanwise variation of placement (4%C and 6%C), chordwise placement (45% C and 55% C), and the angle of attack of 13o using one CAD and three commercially available CFD softwares.
The simulation results found that the modification of the airfoil using a vortex generator near the endwall was able to reduce secondary flow which has an impact on increasing the wing efficiency by 27% over plain airfoil configuration while placed at X/C :0.55 with 13o angle of attack. Also, it was found that the addition of vortex generators were more effective at high angle of attack, rather than 0o angle of attack which shows more detrimental effects towards the performance of the NASA LS-0417 wing.

Item Type:	Thesis (Undergraduate)
Uncontrolled Keywords:	Airfoil, Boundary layer, Coefficient of drag, Coefficient of lift, Stall angle, Vortex Generator
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL507.G77 Vortex generators. T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic.
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Joshua Clarence Sean
Date Deposited:	09 Feb 2022 08:05
Last Modified:	09 Feb 2022 08:05
URI:	http://repository.its.ac.id/id/eprint/93414

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