Numerical Analysis of the Aerodynamic Characteristics of NACA 2413 Airfoil

Abstract

The current investigation primarily focuses on the variability of the aerodynamic characteristics of the NACA-2413 airfoil for different turbulent models (Realizable k-ε Model, Standard k-ε Model, and Shear-Stress Transport (SST) k-ω Model) in different Reynolds Numbers. The aerodynamic characteristics such as lift force, drag force, lift-to-drag ratio, and pressure distribution were evaluated at several angles of attack for different Reynolds numbers (Re = 7×105, 3×106, and 6×106) using Ansys Fluent 2020R2. The numerical results indicate that the lift coefficient increased with the angle of attack up to the stalling point. Though the different turbulent models exhibited nearly the same value at a lower angle of attack, however, produced different values for the higher angles of attack (at ????=10° for Re = 3×106), which is also visible in the velocity and pressure contours. Again, at the lower Reynolds number, the different turbulent model shows considerably different value but this difference is reduced with the increase in Reynolds number. For all the conditions, the k-ε model produces a higher lift value in comparison to the SST k-ꞷ model. However, in the SST k-ꞷ model, separation occurs at a smaller angle of attack as compared to the other two models, because the SST k-ꞷ model more accurately resolves the viscous layer and flow separation for high-pressure gradients than the other two models. Furthermore, with the increase in Reynolds number, the deviation between these three turbulent models decreases significantly. At high Reynolds numbers, the realizable k- ε model and the standard k- ε model produce nearly identical results.