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0 ResultsCFD study of airflow over an 8m chord NACA 0012 aerofoil. Initial case: 10m/s freestream velocity and 0 degrees angle of attack.
by mwavinyamwavinya
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
by ahmedhussain18ahmedhussain18
jtait06 created this project
9 days ago
0 Geometries 0 Meshes 0 Simulation setups 0 ResultsCFD study of airflow over an 8m chord NACA 0012 aerofoil. Initial case: 10m/s freestream velocity and 0 degrees angle of attack.
