Studi Eksperimental Pengaruh Silinder Sirkuler sebagai Pengontrol Pasif Terhadap Kinerja Airfoil NACA 0026 "Studi Kasus Rasio Diameter d/t = 1,0; Rasio Jarak R/c = 0,5; Variasi Sudut Penempatan Silinder = -45°, -30°, -15°, 0°, 15°, 30°, 45°; Variasi Kecepatan Angin 6 dan 12 m/s"

Aisyah, Fadhiani (2026) Studi Eksperimental Pengaruh Silinder Sirkuler sebagai Pengontrol Pasif Terhadap Kinerja Airfoil NACA 0026 "Studi Kasus Rasio Diameter d/t = 1,0; Rasio Jarak R/c = 0,5; 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

Bertambahnya kebutuhan energi bersih dan energi terbarukan mendorong peningkatan efisiensi instrumen aerodinamika, termasuk optimalisasi performa airfoil simetris NACA 0026 melalui pengendalian aliran secara pasif. Penelitian ini bertujuan menilai pengaruh silinder sirkuler sebagai pengontrol pasif terhadap kinerja NACA 0026 pada angle of attack (AOA) 0°. Studi kasus menggunakan diameter silinder d = 39 mm dengan rasio diameter dengan thickness airfoil sebesar 1.0 dan rasio jarak penempatan silinder dengan chord sebesar 0.5. Metode yang digunakan berupa pengujian eksperimental menggunakan wind tunnel subsonik dengan dua kecepatan aliran, 6 m/s dan 12 m/s. Silinder ditempatkan pada tujuh sudut terhadap leading edge, yaitu −45°, −30°, −15°, 0°, 15°, 30°, 45°. Distribusi tekanan pada permukaan airfoil diukur menggunkana pressure tap yang terhubung dengan manometer digital Fluke 992, sedangkan gaya aerodinamika diukur menggunakan force balance. Data yang diperoleh meliputi pemetaan distribusi koefisien tekanan (Cp) pada permukaan airfoil dan pengukuran gaya aerodinamika untuk menghitung koefisien angkat (CL), koefisien hambat (CD) dan rasio CL/CD. Hasil penelitian menunjukkan bahwa penambahan silinder sirkuler mampu menghasilkan gaya angkat pada airfoil simetris NACA 0026 yang semula memiliki nilai C_L bernilai 0 pada angle of attack 0°. Nilai C_L tertinggi diperoleh pada sudut stagger -15°, yaitu sebesar 0,227 pada kecepatan 6 m/s dan 0,169 pada kecepatan 12 m/s. Rasio C_L/C_Djuga diperoleh pada sudut stagger -15° dengan nilai C_L/C_D sebesar 0,340 pada kecepatan 6 m/s dan 0,488 pada kecepatan 12 m/s. Namun, seluruh konfigurasi silinder menghasilkan nilai C_Dyang lebih tinggi dibandingkan plain airfoil, sehingga tujuan pengurangan gaya hambat belum berhasil dicapai. Dengan demikian penambahan silinder sirkuler terbukti efektif untuk menghasilkan gaya angkat dan meningkatkan performa aerodinamika airfoil NACA 0026 pada angle of attack 0°, dengan konfigurasi optimum pada sudut stagger -15°.
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The growing demand for clean energy and renewable energy is driving improvements in the efficiency of aerodynamic devices, including the optimization of the performance of the NACA 0026 symmetric airfoil through passive flow control. This study aims to evaluate the effect of a circular cylinder as a passive controller on the performance of the NACA 0026 at an angle of attack (AOA) of 0°. The case study uses a cylinder diameter d = 39 mm with a diameter-to-airfoil-thickness ratio of 1.0 and a ratio of the cylinder’s placement distance to the chord length of 0.5.
The method employed involved experimental testing using a subsonic wind tunnel at two flow speeds: 6 m/s and 12 m/s. The cylinder was positioned at seven angles relative to the leading edge: −45°, −30°, −15°, 0°, 15°, 30°, and 45°. The pressure distribution on the airfoil surface was measured using a pressure tap connected to a Fluke 992 digital manometer, while the aerodynamic forces were measured using a force balance. The data obtained includes a mapping of the pressure coefficient (Cp) distribution on the airfoil surface and measurements of aerodynamic forces to calculate the lift coefficient (C_L), drag coefficient 〖(C〗_D), and the C_L/C_D ratio. The results of the study show that the addition of circular cylinders is capable of generating lift on a symmetric NACA 0026 airfoil that originally had a C_L value of 0 at an angle of attack of 0°. The highest C_Lvalue was obtained at a stagger angle of -15°, namely 0.227 at a speed of 6 m/s and 0.169 at a speed of 12 m/s. The C_L/C_D ratio was also obtained at a stagger angle -15°, with C_L/C_D values of 0.340 at a speed of 6 m/s and 0.488 at a speed of 12 m/s. However, all cylinder configurations resulted in higher C_D values compared to the plain airfoil, so the goal of reducing drag was not achieved. Thus, the addition of circular cylinders proved effective in generating lift and improving the aerodynamic performance of the NACA 0026 airfoil at an angle of attack of 0°, with the optimal configuration at a stagger angle of -15°.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Airfoil NACA 0026, Silinder Sirkuler, Kontrol Aliran Pasif, Circular Cylinder, NACA 0026 Airfoil, Passive Flow Control
Subjects:	Q Science > Q Science (General) T Technology > TJ Mechanical engineering and machinery > TJ808 Renewable energy sources. Energy harvesting. T Technology > TJ Mechanical engineering and machinery > TJ820 Wind power T Technology > TJ Mechanical engineering and machinery > TJ828 Wind turbines
Divisions:	Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Fadhiani Aisyah
Date Deposited:	27 Jul 2026 07:47
Last Modified:	27 Jul 2026 07:47
URI:	http://repository.its.ac.id/id/eprint/138033

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