Studi Numerik Pengaruh Posisi Vortex Generator di Dekat Endwall Terhadap Pengendalian Aliran Sekunder pada Airfoil NASA LS-0417

Galunggung, Resnu Caesio Oratory (2022) Studi Numerik Pengaruh Posisi Vortex Generator di Dekat Endwall Terhadap Pengendalian Aliran Sekunder pada Airfoil NASA LS-0417. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Industri pesawat terbang dipicu untuk dapat memproduksi pesawat terbang yang lebih efisien. Salah satu kerugian pada airfoil diakibatkan oleh interaksi antara endwall dan airfoil. Studi terdahulu menunjukkan bahwa penambahan vortex generator pada airfoil NASA LS-0417 yang diletakkan dekat dengan endwall dapat meningkatkan nilai lift coefficient pada sudut serang tertentu.
Penelitian ini merupakan studi simulasi numerik tiga dimensi menggunakan perangkat lunak Ansys Fluent untuk mengetahui efek posisi vortex generator di dekat endwall terhadap kualitas reduksi separasi tiga dimensi pada airfoil NASA LS-0417 dengan panjang chord 10 cm dan aspect ratio 5, penempatan vortex generator terdapat pada 45%, 50%, 55% chordwise serta 0.4% dan 0.6% spanwise. Simulasi menggunakan model k-ω Shear Stress Transfer dengan fluida kerja udara yang dengan bilangan Reynolds 1 x 105 pada kondisi steady.
Hasil dari simulasi yang dilakukan adalah vortex generator dapat mereduksi aliran sekunder. Hal tersebut mengakibatkan peningkatan Cl/Cd terbesar pada penempatan vortex generator di x/c = 0.45 dan z = 0.4% sebesar 7.3%, sementara penurunan total pressure losses coefficient terbesar berada pada penempatan vortex generator di x/c = 0.45 dan z = 0.4%C sebesar 28.6%.
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The biggest challange in aviation industry is to increase efficiency. One of modern airplane’s biggest losses comes from the interaction between the endwall and the airfoil. Previous study shows that the addition vortex generators near the endwall can improve the lift coefficient of NASA LS-0417 airfoils especially at specific angle of attacks due to delaying of separation at the airfoil.
This research is a three dimensional numerical simulation using the Ansys Fluent software to discover the effect of vortex generator placed near endwall at different positions to the quality of three-dimensional separation at NASA LS-0417 airfoil with a chord length of 10 cm and aspect ratio of 5, the vortex generators are located at 45%, 50%, 55% chordwise and also 0.4% and 0.6% spanwise. The simulation is using k-ω Shear Stress Transfer model with air as working fluid that flows at Reynolds number of 1 x 105 in steady conditions.
This research shows that vortex generator can reduce the secondary flow which results in improvements of Cl/Cd at its biggest value of 7.3% by the placement of vortex generator at x/c = 0.45 and z = 0.4%C, and also reduction of total pressure losses coefficient at its biggest of 28.6% which is produced by placement of vortex generator at the same location as before.

Item Type:	Thesis (Undergraduate)
Uncontrolled Keywords:	Airfoil, vortex generator, sudut serang, separasi tiga dimensi
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:	Resnu Caesio Oratory Galunggung
Date Deposited:	13 Feb 2022 14:41
Last Modified:	13 Feb 2022 14:41
URI:	http://repository.its.ac.id/id/eprint/93901

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