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1 Geometry
1 Mesh
1 Simulation setup
0 ResultsAerodynamic lift and drag polar sweep for NACA 4412 airfoil at $Re = 1 \times 10^6$.
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by mwavinyamwavinya
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
Isuri16 created this project
1 Geometry 1 Mesh 1 Simulation setup 0 ResultsAerodynamic lift and drag polar sweep for NACA 4412 airfoil at $Re = 1 \times 10^6$.
