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Analysis of NACA 4412 Aerofoil using Computational Fluids in Ansys Software


Kaushal Shrivastava , SAMRAT ASHOK TECHNOLOGICAL INSTITUTE, VIDISHA (M.P.); Prof Sandeep Jain, Samrat Ashok Technological Institute, Vidisha (M.P.); Dr. Lokesh Bajpai, Samrat Ashok Technological Institute, Vidisha (M.P.)


Airfoil, Coefficient of Drag, Coefficient of Lift, CFD


This paper focuses primarily on some specific parameters (like coefficient of drag, coefficient of lift, pressure and velocity variation) that mainly effects aerodynamic efficiency of aerofoil. The airfoil of a plane has crucial influence on its aerodynamic efficiency, hence the selection of a suitable airfoil section for the plane is of utmost importance. In this paper, National Advisory Committee for Aeronautics (NACA) 4412 airfoil profile is considered for analysis of its various parameters. The geometry of the airfoil is created using ANSYS16.2 and CFD analysis is carried out using CFX at 40 and 80 angle of attack (AOA). The coefficient of lift and drag values are calculated for 1 ×105 Reynolds number.

Other Details

Paper ID: IJSRDV4I70174
Published in: Volume : 4, Issue : 7
Publication Date: 01/10/2016
Page(s): 411-413

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