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

Abstract

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

NumericalStudy of Turbulent Flows over a NACA 0012 Airfoil: Insights into Its Performance and the Addition of a Slotted Flap

“…Finally, the stock NACA 0012 is extended into a 3D model; one 3D model has an airfoil spanning the entire domain and the other partially spans a larger domain, creating a wingtip. The 3D models are compared to the 2D model and to each other [16][17][18][19].…”