STUDI AERODINAMIKA DAMPAK TERJADINYA ICING PADA AIRFOIL NACA 2412 DENGAN MENGGUNAKAN COMPUTATIONAL FLUID DYNAMIC
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Jourdy Ardi Pratama, I Putu
Subject
T Technology (General)
Datestamp
2024-02-15 08:22:02
Abstract :
NACA 2412 airfoil model manufacturing without ice or with the addition of ice is the basic form of an aircraft wing which aims to provide the aircraft's lift while flying. Lift occurs due to differences in air velocity and pressure at the top and bottom of the wing. Each type of airfoil has different characteristics and coefficient values. Research on the phenomenon of ice formation around the airfoil can be carried out using two methods, namely, wind tunnel testing and software-based computational testing. The research process was carried out using the Computational Fluid Dynamic 2D simulation method using the Ansysfluent software and also supported by the AutoCad 2016 software. The simulation was carried out on an asymmetrical airfoil of the NACA 2412 type with the phenomenon of adding ice on the leading edge and varying the angle of attack of the airfoil. The simulation parameter settings were carried out in accordance with the original conditions. The output of this simulation was the value of lift coefficient, drag coefficient, streamlined contour, pressure point, and air velocity. The results research indicated that the NACA 2412 airfoil had the maximum angle of attack at 15o . The addition of ice decreased the angle of attack by 12o . This was because the ice phenomenon could reduce the value of the lift coefficient.
NACA 2412 airfoil model manufacturing without ice or with the addition of ice is the basic form of an aircraft wing which aims to provide the aircraft's lift while flying. Lift occurs due to differences in air velocity and pressure at the top and bottom of the wing. Each type of airfoil has different characteristics and coefficient values. Research on the phenomenon of ice formation around the airfoil can be carried out using two methods, namely, wind tunnel testing and software-based computational testing. The research process was carried out using the Computational Fluid Dynamic 2D simulation method using the Ansysfluent software and also supported by the AutoCad 2016 software. The simulation was carried out on an asymmetrical airfoil of the NACA 2412 type with the phenomenon of adding ice on the leading edge and varying the angle of attack of the airfoil. The simulation parameter settings were carried out in accordance with the original conditions. The output of this simulation was the value of lift coefficient, drag coefficient, streamlined contour, pressure point, and air velocity. The results research indicated that the NACA 2412 airfoil had the maximum angle of attack at 15o . The addition of ice decreased the angle of attack by 12o . This was because the ice phenomenon could reduce the value of the lift coefficient.
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