Studi Eksperimental Pengaruh Pemasangan Riblet Segitiga Terhadap Perubahan Karakteristik Aliran Pada Airfoil Simetri NACA 0026 “Studi Kasus Triangle Riblet Ukuran S = H = 1 mm x/c = 25%-40% Arah Longitudinal Posisi Protruded”

Istifasha, Alvadyo Ghazi (2026) Studi Eksperimental Pengaruh Pemasangan Riblet Segitiga Terhadap Perubahan Karakteristik Aliran Pada Airfoil Simetri NACA 0026 “Studi Kasus Triangle Riblet Ukuran S = H = 1 mm x/c = 25%-40% Arah Longitudinal Posisi Protruded”. Other thesis, Institut Teknologi Sepuluh November.

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Abstract

6019232003Pengendalian aliran pada permukaan airfoil merupakan salah satu upaya untuk meningkatkan performa aerodinamika, khususnya dalam menghasilkan gaya angkat yang optimal. Salah satu metode yang dikembangkan adalah penambahan riblet pada permukaan airfoil untuk memodifikasi karakteristik lapisan batas. Penelitian ini bertujuan untuk menganalisis dampak dari instalasi riblet dengan geometri Triangle-V yang memiliki dimensi s = h = 1 mm dan dipasang pada riblet pada 25%-35% panjang chord secara longitudinal pada area permukaan atas airfoil NACA 0026 ditinjau dari koefisien lift (CL) dan distribusi koefisien tekanan (Cp). Pengujian dilakukan secara eksperimental menggunakan terowongan angin dengan variasi kecepatan aliran 8 m/s, 12 m/s, dan 16 m/s serta variasi sudut serang −10°, −5°, 0°, 5°, dan 10°. Data distribusi tekanan diukur menggunakan micromanometer pada beberapa titik sepanjang chord airfoil dan perhitungan CL diperoleh dengan perhitungan trapezoida dari Cp yang sudah di dapat. Hasil pengujian menunjukkan nilai CL pada kecepatan rendah, penambahan riblet cenderung menurunkan nilai CL dibandingkan airfoil polos. Pada kecepatan menengah, pengaruh riblet relatif kecil dan belum signifikan. Namun, pada kecepatan tinggi, airfoil dengan riblet menunjukkan peningkatan nilai CL. Distribusi Cp menunjukkan bahwa pada kecepatan tinggi, airfoil riblet menghasilkan selisih tekanan yang lebih besar antara permukaan atas dan bawah, sehingga meningkatkan gaya angkat. Dengan demikian, penambahan riblet efektif meningkatkan performa aerodinamika airfoil pada kecepatan tinggi dengan selisih antara polos dan penambahan riblet sebesar 2% dan 2,3%.
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Flow control on the surface of an airfoil is one of the approaches used to enhance aerodynamic performance, particularly in generating optimal lift. One method that has been developed is the application of riblets on the airfoil surface to modify boundary layer characteristics. This study aims to analyze the effect of installing Triangle-V geometry riblets with dimensions of s = h =1 mm, positioned longitudinally at 25%–35% of the chord length on the upper surface of a NACA 0026 airfoil, in terms of the lift coefficient (CL) and pressure coefficient (Cp) distribution. Experimental testing was conducted using a wind tunnel with flow velocities of 8 m/s, 12 m/s, and 16 m/s, and angles of attack of −10°, −5°, 0°, 5°, and 10°. Pressure distribution data were obtained using a micromanometer at several measurement points along the airfoil chord, and the lift coefficient was calculated using trapezoidal numerical integration of the measured Cp values. The results indicate that at low flow velocities, the addition of riblets tends to reduce the lift coefficient compared to the smooth airfoil. At intermediate velocities, the effect of riblets is relatively small and not yet significant. However, at high flow velocities, the airfoil with riblets exhibits an increase in lift coefficient. The Cp distribution shows that at high velocities, the riblet-equipped airfoil produces a greater pressure difference between the upper and lower surfaces, thereby enhancing lift. Thus, the application of riblets is effective in improving the aerodynamic performance of the airfoil at high velocities, with lift coefficient differences between the smooth and riblet configurations of approximately 2% and 2.3%.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	airfoil NACA 0026, riblet, koefisien lift, koefisien tekanan, aerodinamika, NACA 0026 airfoil, riblet, lift coefficient, pressure coefficient, aerodynamics.
Subjects:	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:	Alvadyo Ghazi Istifasha
Date Deposited:	03 Feb 2026 09:44
Last Modified:	03 Feb 2026 09:44
URI:	http://repository.its.ac.id/id/eprint/131874

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