Purba, Fridolin Wahyu (2024) Studi Eksperimen Karakteristik Aliran Fluida Melewati Single Slotted Flap NACA 23012 Airfoil dengan Variasi Flap Deflection Angle 0º, 10º, 20º, 30º, dan 40º. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Sayap merupakan komponen terpenting pesawat terbang dalam menghasilkan gaya lift. Gaya lift yang terjadi pada sayap terjadi karena geometri sayap yang disebut airfoil yang memungkinkan aliran udara yang mengalir melalui permukaan atas sayap bergerak lebih cepat daripada aliran udara yang mengalir melalui permukaan bawah sayap yang menyebabkan adanya perbedaan tekanan dan menghasilkan gaya lift. Nilai gaya lift meningkat seiring bertambahnya angle of attack sebelum akhirnya menurun dan menyebabkan stall. Peningkatan gaya lift ini juga diikuti dengan peningkatan gaya drag. Meningkatnya gaya drag terjadi akibat separasi aliran yang menyebabkan terbentuknya wake region. Salah satu hal yang dilakukan untuk meningkatkan gaya lift ini adalah dengan menambahkan single slotted flap pada sayap. Gap antara main wing dan flap pada single slotted flap memungkinkan aliran fluida dari permukaan bawah sayap bergerak naik dan memberikan momentum tambahan untuk menunda separasi aliran. Penelitian ini dilakukan dengan analisa berbasis eksperimen pada pengaruh penambahan single slotted flap pada sayap terhadap karakteristik aliran udara yang melewatinya. Penelitian ini dilakukan dengan menggunakan wind tunnel yang berada di Departemen Teknik Mesin FTIRS-ITS dengan kecepatan freestream 10 m/s. Model benda uji yang akan digunakan menggunakan NACA 23012 sebagai airfoil-nya dengan panjang chord (c) 240 mm. Variasi flap deflection angle (δF) yang diberikan adalah 0º, 10º, 20º, 30º, dan 40º dengan gap antara main wing dan flap tetap sebesar 2,5%c. Model benda uji diuji pada angle of attack (α) 0º, 8º, 14º, 16º, 17º dan 20º untuk pengukuran gaya drag dan lift, serta pada angle of attack (α) 0º, 14º, dan 20º untuk pengukuran profil kecepatan pada jarak 1c (240 mm) dari trailing edge sayap. Berdasarkan hasil penelitian ditemukan bahwa penambahan single slotted flap dengan variasi flap deflection angle meningkatkan koefisien lift (CL) dan koefisien drag (CD) yang dihasilkan setiap benda uji. Nilai ini meningkat seiring bertambahnya flap deflection angle dan angle of attack. Koefisien lift terbesar dihasilkan oleh variasi flap deflection angle 40° pada sudut α = 14° dengan nilai 1,273. Nilai ini meningkat sebesar 0,62 dari nilai koefisien lift maksimum plain airfoil. Koefisien drag tertinggi dihasilkan oleh variasi flap deflection angle 40° pada sudut α = 20° dengan nilai 0,422. Nilai CL/CD tertinggi dihasilkan oleh plain airfoil pada sudut α = 14° dengan nilai 8,531. Pada sudut α = 0°, nilai CL/CD tertinggi dihasilkan oleh variasi flap deflection angle 30° dengan nilai 5,131.
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The wing is the most important component of an airplane in generating lift. The lift force that occurs on the wing occurs due to the geometry of the wing called an airfoil which allows the airflow flowing through the upper surface of the wing to move faster than the airflow flowing through the lower surface of the wing. This phenomenon causes pressure difference between the lower and upper surface ot the wing and leads to generate lift force. The value of the lift force increases as the angle of attack increases before finally decreasing and causing a stall. This increase in lift force is also followed by an increase in drag force. The increase in drag force occurs due to flow separation which causes the formation of a wake region. One method that can be used to increase the lift force is by adding a single slotted flap to the wing. The gap between the main wing and the flap on the single slotted flap allows fluid flow from the lower surface of the wing to move up to upper surface of the wing and provides additional momentum to fluid flow on the upper surface and delays flow separation. This research was conducted experimentally to evaluate the effect of the addition of a single slotted flap on the flow characteristics around the wing. This research was conducted using a wind tunnel located at the Department of Mechanical Engineering INDSYS-ITS with freestream velocity of 10 m/s. The model to be used is NACA 23012 airfoil with a chord length (c) of 240 mm. The flap deflection angles are 0º, 10º, 20º, 30º, and 40º with the gap between the main wing and flap fixed at 2.5%c. The model was tested at angles of attack 0º, 8º, 14º, 16º, 17º, and 20º for drag and lift force measurements, and at angles of attack 0º, 14º, and 20º for velocity profile measurements at 1c (240 mm) behind the wing trailing edge. Based on the results of the study, it was found that the addition of single slotted flap with flap deflection angle variations can be able to increase the wing lift coefficient (CL). This lift coefficient (CL) increases as the flap deflection angle and angle of attack increase. The highest lift coefficient is produced by the 40° flap deflection angle variation at α = 14° with a value of 1.273. This value increases by 0.62 from the maximum lift coefficient of the plain airfoil. The highest drag coefficient is produced by the 40° flap deflection angle variation at angle α = 20° with a value of 0.422. The highest CL/CD value is produced by the plain airfoil at angle α = 14° with a value of 8.531. At angle α = 0°, the highest CL/CD value is produced by the 30° flap deflection angle variation with a value of 5.131.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Airfoil, Drag Coefficient, Flap Deflection Angle, Lift Coefficient, Single Slotted Flap |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL673.F6 Flaps (Airplane) |
| Divisions: | Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Fridolin Wahyu Purba |
| Date Deposited: | 12 Feb 2024 00:13 |
| Last Modified: | 12 Feb 2024 00:13 |
| URI: | http://repository.its.ac.id/id/eprint/106905 |
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