Studi Eksperimental Pengaruh Silinder Sirkuler Sebagai Pengontrol Pasif Terhadap Kinerja Airfoil NACA 0026 “Studi Kasus untuk Rasio Diameter d/t = 1,0 dan Rasio Jarak R/C = 0,70”

Adiputra, Rayhan (2026) Studi Eksperimental Pengaruh Silinder Sirkuler Sebagai Pengontrol Pasif Terhadap Kinerja Airfoil NACA 0026 “Studi Kasus untuk Rasio Diameter d/t = 1,0 dan Rasio Jarak R/C = 0,70”. Other thesis, Institut Teknologi Sepuluh Nopember.

Text 5007211166 -Undergraduate_Thesis.pdf - Accepted Version Restricted to Repository staff only Download (5MB) | Request a copy

Abstract

Perkembangan teknologi turbin angin skala kecil mendorong kebutuhan akan airfoil yang efisien pada bilangan Reynolds rendah hingga menengah. Airfoil NACA-0026 bersifat simetris dengan ketebalan maksimum 26% chord sehingga rentan terhadap separasi aliran akibat adverse pressure gradient, yang menurunkan lift dan efisiensi aerodinamis. Passive flow control menggunakan silinder sirkuler menjadi solusi alternatif yang menarik karena mampu me-re-energize boundary layer tanpa energi eksternal. Penelitian ini bertujuan mengkaji pengaruh variasi sudut penempatan silinder terhadap kinerja aerodinamis airfoil NACA-0026 dan menentukan konfigurasi optimal. Penelitian dilakukan secara eksperimental di wind tunnel menggunakan airfoil NACA-0026 (chord 150 mm, span 250 mm, AoA = 0°). Silinder berdiameter d = 39 mm (d/t = 1,0) dipasang pada R = 105 mm dari leading edge dengan variasi sudut θ = −45° hingga +45° (interval 15°) dan kecepatan aliran 6 m/s serta 12 m/s. Pengukuran menggunakan force balance, pressure taps, dan pitot tube untuk profil wake pada jarak 4C di belakang airfoil. Hasil menunjukkan CL terbesar pada θ = ±45° (6 m/s, CL = +0,161) dan θ = ±30° (12 m/s, CL = +0,091), sedangkan CL terkecil pada θ = 0° dan θ = ±15° pada dua kecepatan. CD terendah di antara konfigurasi bersilinder diperoleh pada θ = 0°, namun tetap jauh lebih besar dibandingkan plain airfoil. Rasio CL/CD terbaik diperoleh pada θ = ±45° (6 m/s, +0,4237) dan θ = ±30° (12 m/s, +0,3319). Hasil ini menunjukkan bahwa variasi posisi silinder memengaruhi karakteristik aerodinamika airfoil NACA 0026.
=======================================================================================================================================
The development of small-scale wind turbine technology has driven the need for airfoils that operate efficiently at low to moderate Reynolds numbers. The NACA-0026 airfoil is symmetric with a maximum thickness of 26% chord, making it prone to flow separation due to adverse pressure gradient, which reduces lift and aerodynamic efficiency. Passive flow control using a circular cylinder is an attractive alternative solution, as it can re-energize the boundary layer without requiring external energy. This study aims to examine the effect of circular cylinder placement angle variation on the aerodynamic performance of the NACA-0026 airfoil and to determine the optimal configuration. The research was conducted experimentally in a wind tunnel using a NACA-0026 airfoil (chord 150 mm, span 250 mm, AoA = 0°). A cylinder with diameter d = 39 mm (d/t = 1.0) was placed at R = 105 mm from the leading edge, with angle variations θ = −45° to +45° (15° intervals) and two freestream velocities, 6 m/s and 12 m/s. Measurements were taken using a force balance, pressure taps, and a pitot tube for the wake velocity profile at 4C behind the airfoil. The results show that the highest lift coefficient (CL) was obtained at θ = +45° (6 m/s, CL = +0.161) and θ = +30° (12 m/s, CL = +0.091), whereas the lowest CL was observed at θ = 0° and θ = ±15° for both flow velocities. Among the cylinder-equipped configurations, the lowest drag coefficient (CD) was achieved at θ = 0°, although it remained considerably higher than that of the plain airfoil. The highest CL/CD ratio was obtained at θ = +45° (6 m/s, 0.4237) and θ = +30° (12 m/s, 0.3319). These findings indicate that variations in cylinder placement significantly influence the aerodynamic characteristics of the NACA 0026 airfoil.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Airfoil NACA-0026, silinder sirkuler, passive flow control, koefisien lift, koefisien drag.NACA-0026 airfoil, circular cylinder, passive flow control, lift coefficient, drag coefficient
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions:	Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Rayhan Adiputra
Date Deposited:	03 Aug 2026 07:33
Last Modified:	03 Aug 2026 07:33
URI:	http://repository.its.ac.id/id/eprint/142169

Actions (login required)

View Item