Comparison of Pressure Distribution of Naca 0012 Between CFD Code and Experimental

Computational Fluid Dynamics (CFD) is a tool to solve engineering problem. Commercial CFD code are being used most problem but rarely for external aerodynamic due some limitation of features. Compare in house that able written certain area interest and also implement specific discretization scheme increase accuracy. In this work, the developed by using high resolution (ROE TVD scheme) flow past through airfoil NACA 0012. Experimental result wind tunnel obtained from literature which Gregory O’Reilly at Mach number M = 0.13 different values angle attack α= 0° α 10°. Another Haris 0.8 angles 3.86°. Comparison results both codes indicate give closest experimental.