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- In this book , a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with
the given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD)
analysis were performed using FLUENT in ANSYS. The Reynolds number based on the chord is
roughly 𝑅 𝑒 = 2.88 × 106. The flow was modeled as incompressible and inviscid. All setup and
procedures were done by following the steps provided Cornel University website. Though, mesh
independence was achieved for 2° attack angle, for 14° attack angle which is more than the stall angle, mesh independence was not achieved. Lift and drag coefficient increases as the number of mesh element or the attack angle increases.-In this book , a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with
the given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD)
analysis were performed using FLUENT in ANSYS. The Reynolds number based on the chord is
roughly 𝑅 𝑒 = 2.88 × 106. The flow was modeled as incompressible and inviscid. All setup and
procedures were done by following the steps provided Cornel University website. Though, mesh
independence was achieved for 2° attack angle, for 14° attack angle which is more than the stall angle, mesh independence was not achieved. Lift and drag coefficient increases as the number of mesh element or the attack angle increases.
Update : 2025-04-12 Size : 3.52mb Publisher : ahmed