Simulasi Numerik Efek Riblet Segitiga Ukuran (S = H = 1 mm) Aligned Arah Transversal Dipasang Sepanjang 25–30% Panjang Chord Pada Aliran Di Dekat Permukaan Airfoil NACA 0026

Irsa, Athallah Naufal (2025) Simulasi Numerik Efek Riblet Segitiga Ukuran (S = H = 1 mm) Aligned Arah Transversal Dipasang Sepanjang 25–30% Panjang Chord Pada Aliran Di Dekat Permukaan Airfoil NACA 0026. Other thesis, Institut Teknologi Sepuluh Nopember.

Text 5007211192-Undergradate_Thesis.pdf Restricted to Repository staff only Download (8MB) | Request a copy

Abstract

Pengurangan drag pada airfoil merupakan fokus penting dalam pengembangan efisiensi aerodinamika. Salah satu metode yang digunakan adalah pemasangan riblet, struktur mikro berbentuk alur, pada permukaan airfoil. Penelitian ini menyelidiki efek riblet segitiga tipe transversal dengan dimensi 1 mm yang dipasang pada 25–30% panjang chord airfoil NACA 0026. Simulasi dilakukan menggunakan Computational Fluid Dynamics (CFD) berbasis ANSYS Fluent dengan model turbulensi k-ε dan variasi kecepatan 8, 12, dan 16 m/s serta angle of attack -15° hingga 15°.
Simulasi terdiri dari tahapan pembuatan geometri, meshing, penentuan boundary condition, serta pemrosesan dan analisis hasil. Parameter yang diamati meliputi koefisien lift, drag, distribusi tekanan, kecepatan, dan lift-to-drag ratio. Diharapkan, riblet mampu menunda separasi aliran dan meningkatkan kinerja aerodinamika airfoil. Hasil penelitian ini dapat menjadi referensi pengembangan desain airfoil untuk aplikasi kecepatan rendah hingga menengah.
Hasil simulasi menunjukkan bahwa airfoil dengan riblet mampu meningkatkan CL maksimum, terutama pada kecepatan 8 m/s dan 12 m/s. Dari sisi gaya hambat, riblet terbukti efektif mengurangi CD pada sudut serang kecil (berkisar antara -5° hingga +5°) untuk kecepatan 8 m/s dan 12 m/s. Namun, pada sudut serang yang lebih tinggi, airfoil riblet justru menunjukkan peningkatan drag yang signifikan dibandingkan airfoil polos.
Efisiensi aerodinamika (CL/CD) menunjukkan peningkatan paling signifikan seiring kenaikan kecepatan; pada 16 m/s, airfoil riblet mencapai rasio (CL/CD) puncak sekitar 25, mengungguli airfoil polos yang hanya mencapai nilai 23. Analisis kontur tekanan dan kecepatan juga mengonfirmasi bahwa riblet mampu mempertahankan daya isap (suction) di dekat leading edge pada sudut serang tinggi, yang berkontribusi pada penundaan stall.
Secara keseluruhan, penelitian ini menyimpulkan bahwa penggunaan riblet pada airfoil NACA 0026 menawarkan peningkatan performa aerodinamika, khususnya dalam hal efisiensi pada kecepatan yang lebih tinggi, meskipun terdapat konsekuensi berupa peningkatan drag pada sudut serang yang besar.
=======================================================================================================================================
Drag reduction on airfoil is an important focus in developing aerodynamic efficiency. One method used is the installation of riblets, groove-shaped microstructures, on the airfoil surface. This study investigates the effect of transverse-type triangular riblets with dimensions of 1 mm installed at 25–30% of the chord length of the NACA 0026 airfoil. Simulations were performed using Computational Fluid Dynamics (CFD) based on ANSYS Fluent with a k-ε turbulence model and speed variations of 8, 12, and 16 m/s and an angle of attack of -15° to 15°.
The simulation consists of the stages of geometry creation, meshing, boundary condition determination, and processing and analysis of the results. The parameters observed include lift coefficient, drag, pressure distribution, speed, and lift-to-drag ratio. It is expected that the riblets are able to maintain flow separation and improve the aerodynamic performance of the airfoil. The results of this study can be a reference for developing airfoil designs for low to medium speed applications.
Simulation results show that riblet airfoils can increase maximum CL, especially at speeds of 8 m/s and 12 m/s. In terms of drag, riblets are effective in reducing CD at low angles of attack (ranging from -5° to +5°) for speeds of 8 m/s and 12 m/s. However, at higher angles of attack, riblet airfoils exhibit a significant increase in drag compared to plain airfoils.
Aerodynamic efficiency (CL/CD) shows the most significant increase with increasing speed; at 16 m/s, riblet airfoils reach a peak CL/CD ratio of approximately 25, outperforming plain airfoils, which only reach a value of 23. Analysis of pressure and velocity contours also confirms that riblets are able to maintain suction near the leading edge at high angles of attack, which contributes to stall delay.
Overall, this study concludes that the use of riblets on the NACA 0026 airfoil offers improved aerodynamic performance, particularly in terms of efficiency at higher speeds, although there is a consequence in the form of increased drag at large angles of attack.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Airfoil, NACA 0026, Riblet, Computational Fluid Dynamic, ANSYS FLUENT
Subjects:	T Technology > T Technology (General) > T57.62 Simulation 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:	Athallah Naufal Irsa
Date Deposited:	31 Jul 2025 09:34
Last Modified:	31 Jul 2025 09:34
URI:	http://repository.its.ac.id/id/eprint/124948

Actions (login required)

View Item