Flow Separation Analysis of a Turbine Blade NACA 63-415

This paper investigate the flow separation behavior of a turbine blade using NACA 63-415 airfoil in three arrangements- without slot, with single slot, with double slot. Computational fluid dynamic simulation are used to study airfoil behavior at 0 to 20 degree angle of attack.to investigate how separation begins and develops. The study targets determination of significant angle of attack at which the flow separation initiates since it influences both the efficiency and performance of the turbine blade. Important aerodynamics factors like pressure distribution, velocity contours and the impact of turbulence are assesses to determine the change in airfoil patterns. Further the research explores whether slot modification at the leading edge are efficient in controlling or postponing flow separation and hence aerodynamic efficiently can be improved. Single and double slot existence is explored to find their effectiveness in enhancing lift to drag ratio, lowering turbulence intensity and ensuring smoother airfoil on the blade surface.