Flow Separation Analysis For Various Angle of Attack on NACA 4412 Aerofoil A Computational Approach

This paper has different parameters of an airfoil (NACA 4412). This paper attempts to discuss the changes in flow characteristics which the surface heating would bring in, when flow takes place over a NACA 4412 airfoil. In this numerical study, the surface heating is quantified using the non-dimensional number called the Richardson number, Ri. A positive value for the Ri indicates surface heating and negative value shows surface cooling. The numerical simulation is done using the commercial CFD package ANSYS Fluent. The investigation is performed for the Richardson number (Ri) ranging -0.5 to 0.7 and at standard sea level conditions. We have considered a single representative Reynolds number of 1x103 at zero angle of attack of the airfoil. It is observed that both surface heating and cooling imparts asymmetry in the flow structure around the airfoil when flow takes place over it. And the surface temperature of the NACA 4412 airfoil has greater influence in the aerodynamic coefficients Cl and Cd.The NACA 4412 airfoil have a higher efficiency at Tip speed ratios of 7. The study of flow over NACA 4412 airfoil is done for the Reynolds number (Re) of 103 and Richardson number (Ri) ranging from -0.5 to +0.7 at zero degree angle of attack.