LATIF, MU'IZA (2026) Studi Eksperimental Pengaruh Silinder Sirkuler Sebagai Pengontrol Pasif Terhadap Kinerja Airfoil Naca 0026 “Studi Kasus untuk Rasio Diameter d/t = 0.5; Rasio Jarak R/c = 0.63; Variasi Sudut Penempatan Silinder = -45°, -30°, -15°, 0°, 15°, 30°, 45°; Variasi Kecepatan Angin 6 dan 12 m/s”. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Separasi aliran pada airfoil simetris tebal seperti NACA 0026 menjadi penyebab utama penurunan efisiensi aerodinamika akibat meningkatnya drag coefficient (CD), menurunnya lift coefficient (CL), serta berkurangnya rasio CL/CD. Meskipun metode passive flow control telah banyak dikembangkan, studi eksperimental pada airfoil tebal masih terbatas. Penelitian ini bertujuan mengkaji secara eksperimental efektivitas silinder sirkuler sebagai pengontrol pasif pada airfoil NACA 0026 dengan variasi sudut penempatan silinder. Penelitian dilakukan menggunakan wind tunnel dengan variasi sudut silinder θ = −45° hingga 45° pada kecepatan aliran 6 m/s dan 12 m/s. Parameter yang dianalisis meliputi distribusi coefficient of pressure (CP), lift coefficient (CL), drag coefficient (CD), dan rasio CL/CD melalui pressure taps dan manometer untuk mengukur tekanan, force balance mengukur gaya aerodinamika, dan pitot tube dan manometer untuk mengukur profil kecepatan. Hasil penelitian menunjukkan bahwa konfigurasi θ = 0° belum mampu menurunkan drag, sedangkan pada θ = 15° hingga 45° terbentuk nozzle effect yang meningkatkan percepatan aliran. Efektivitas meningkat dari 15° menuju 30°, kemudian menurun pada 45°. Konfigurasi 30° menghasilkan performa terbaik dengan nilai CL/CD tertinggi, menunjukkan bahwa sudut penempatan silinder sangat menentukan efektivitas passive flow control pada airfoil NACA 0026.
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Flow separation over thick symmetric airfoils such as NACA 0026 is one of the primary causes of aerodynamic efficiency loss due to increased drag coefficient (CD), reduced lift coefficient (CL), and decreased CL/CD ratio. Although passive flow control methods have been widely developed, experimental studies on thick airfoils remain limited. This study aims to experimentally investigate the effectiveness of a circular cylinder as a passive flow control device on a NACA 0026 airfoil under various cylinder placement angles. The experiment was conducted using a wind tunnel with cylinder placement angles ranging from θ = −45° to 45° at freestream velocities of 6 m/s and 12 m/s. The analyzed parameters included pressure coefficient distribution (CP), lift coefficient (CL), drag coefficient (CD), and CL/CD ratio, measured using pressure taps and a manometer for pressure measurement, a force balance for aerodynamic force measurement, and a pitot tube coupled with a manometer for velocity profile measurement. The results showed that the θ = 0° configuration was not able to reduce drag, whereas configurations from θ = 15° to 45° produced a nozzle effect that accelerated the flow locally. The effectiveness increased from 15° to 30°, then decreased at 45°. The 30° configuration produced the best aerodynamic performance with the highest CL/CD ratio, indicating that cylinder placement angle strongly determines the effectiveness of passive flow control on the NACA 0026 airfoil.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Airfoil NACA 0026, Silinder Sirkuler, Kontrol Pasif, NACA 0026 Airfoil, Circular Cylinder, Passive Control |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic. |
| Divisions: | Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Mu'iza Kaba Latif |
| Date Deposited: | 04 Aug 2026 00:57 |
| Last Modified: | 04 Aug 2026 00:57 |
| URI: | http://repository.its.ac.id/id/eprint/142808 |
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