This project investigated the transient aerodynamic behavior of a NACA airfoil as the angle of attack was progressively increased at Mach 0.6. CFD simulation was used to visualize the evolution of the airflow and examine how the aerodynamic characteristics changed as the airfoil approached stall.
At lower angles of attack, the flow remained predominantly attached to the airfoil surface. As the incidence increased toward the critical range, adverse pressure gradients intensified and progressive flow separation developed over the suction side. The resulting separated-flow region significantly altered the surface-pressure distribution and weakened the aerodynamic suction responsible for lift, illustrating the transition toward stalled conditions.
The transient CFD analysis provided insight into the development of flow separation rather than examining only isolated steady-state operating points. This made the project particularly useful for aerodynamic research, allowing stall development, streamline behavior, and pressure changes to be investigated throughout the changing angle-of-attack condition.
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