Numerical study of the air flow over modified NACA 2412 airfoil using CFD

An aerodynamic study of air flow effect around different NACA 2412 airfoil geometries was established using methods of CFD. The main focus of work is to improve efficient engineering procedures for analyzing the flow of air around modified NACA 2412 airfoils related to the CFD tools. The coordinates of the airfoil geometry as mentioned in the airfoil database of reference [21], and then importing these coordinates to the geometry modeler. Generating mesh and conduct the experimentation using Fluid Flow (Fluent). The simulation was done by solving the governing equations (Continuity, Reynolds Averaging Navier-Stokes and Energy Equation) in 2-D using Fluent analysis at Reynolds number of 1x106. Based on the results presented, forces of lift and drag has been observed to be increased respectively as increasing the angle of attack till reaching stall. The optimum angle of attack was 4o. At this specified angle, the 2412 downward geometry gives the maximum lift to drag ratio (42.534). The critical or stall angle of attack was 16o. After this angle of attack, the lift force produced from the airfoil body falls gradually and generated region is known as stall. The CFD modeling and simulating which is used in this work is suitable in circulating flow around airfoil models.