Set up your own cloud-native simulation in minutes.Start Simulating Now
0
0
1 Geometry
5 Meshes
1 Simulation setup
1 ResultHigh-fidelity steady-state incompressible flow analysis over a NACA 0012 symmetric airfoil. The study focuses on quantifying lift and drag coefficients ($C_L$, $C_D$) and visualizing pressure distribution ($C_p$) at varying angles of attack (AoA). Validated against experimental NASA Langley wind tunnel data. - Copy
by simscalesimscale
1 Geometry 5 Meshes 1 Simulation setup 1 ResultHigh-fidelity steady-state incompressible flow analysis over a NACA 0012 symmetric airfoil. The study focuses on quantifying lift and drag coefficients ($C_L$, $C_D$) and visualizing pressure distribution ($C_p$) at varying angles of attack (AoA). Validated against experimental NASA Langley wind tunnel data. - Copy
Nikunj_15 created this project
4 months ago
aaron9087yo copied this project
18 days ago
