Abstract:
The paper presents the study of fluid flow analysis of NACA 2412 airfoil having cavities
on its suction surface at different chord wise location from leading edge to trailing edge by
numerical simulation and wind tunnel experiment. In this work, the behavior of a twodimensional model equipped with a span wise adjusted semicircular cavity positioned at
0.25C, 0.50C and 0.75C has been researched and compared with standard NACA 2412
airfoil. The two-dimensional airfoil models were created in SOLIDWORKS and mesh are
created for numerical analysis using ANSYS Meshing, which is executed in Fluent for
numerical iteration solution. The Spallart-Allmaras turbulence model has been used. From
CFD-Post Coefficient of lift (Cl), Coefficient of drag (Cd) and lift to drag ratio, velocity
streamline, velocity vector and coefficient of pressure along the chord length were
monitored. Experimental tests have been performed on four wooden airfoil models at three
different velocities. First the coefficient of lift (Cl), coefficient of drag (Cd) and lift to drag
ratio readings were taken for the standard airfoil for different angles of attack varying the
wind tunnel speed. Then the modified surface airfoil readings were taken at similar flow
conditions. Adding cavity at 0.50C and 0.75C show higher lift coefficient values at all
speeds. Drag coefficient increases with the increase of AoA and is minimum for airfoil
with cavity at 0.50C. A delay of stall is seen for airfoils with cavity at 0.50C and 0.75C.
