A Computational Case Study on Aerodynamic parameters of NACA symmetrical Aerofoils

The objective of this research is to determine the velocity and pressure field of NACA-0022 airfoil by solving the governing equation using Ansys fluent and to validate the result data of 10degree angle of attack of an airfoil with the experimental data provided by NASA such as1)Pressure coefficient. 2)Lift and drag coefficient.Also to determine the stalling angle by changing the angle of attack to 4,6,10,15,19 degree. During the research we found that The NACA 4 digit airfoil have a higher efficiency at Tip speed ratios of 7. The study of flow over NACA 4 digit airfoil is done for the Reynolds number (Re) of 105 and Richardson number (Ri) ranging from -0.5 to +0.7 at zero degree angle of attack. It has been found that with the increase in Ri, the Cl decreases almost linearly. On the contrary with the increase in Ri, the Cd increases. We found that the surface heating results in the early flow separation and is attributed to such behavior for Cl and Cd. Early flow separation leads to broaden the wake width and static pressure distribution around the airfoil modifies which eventually resulting in an increase in Cd and decrease in Cl on heating the airfoil surface.