STUDI COMPUTATIONAL FLUID DYNAMIC TENTANG PENGARUH PENAMBAHAN TRAILING EDGE FLAP PADA NACA SIMETRIS 0021 TERHADAP PERFORMA AIRFOIL

Hisyam, Muhamad (2020) STUDI COMPUTATIONAL FLUID DYNAMIC TENTANG PENGARUH PENAMBAHAN TRAILING EDGE FLAP PADA NACA SIMETRIS 0021 TERHADAP PERFORMA AIRFOIL. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

The airfoils are used to get the lifting force on the design of plane’s wings. The lifting force is caused by difference air velocity on upper and lower airfoil which the magnitude depend on attack angle of aerofoil and air velocity exist surrounding. This research had modeling and simulation of the NACA 0021 airfoil equipped with flap using ANSYS 16.5 software to investigate the value of lift and drag coefficient and to find out the differences between NACA 0021 airfoil equipped with and without flap. The simulation was carried out with the variations of flap deflection and Angle of Attack (AoA). This modeling was carried out on the Computer-Aided Design – Professional Autodesk Inventor 2020, then simulated in the ANSYS software with the specified settings and parameters. The simulation results were in the form of lift coefficient, drag coefficient, contour, and streamline. The research showed that the airfoil with the addition of flap produced the higher lift and drag coefficient rather than the airfoil without flap and an increase also followed an increase in AoA in the lift and drag coefficient until it reached the stall point at 14°. The maximum lift coefficient on 30 ° airfoil flap occurred at 13 ° AoA.

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