airfoil -- CFD Online Discussion Forums

June 22, 2004, 07:22	airfoil	#1
new Guest Posts: n/a	Hi! I'm trying to get values of cd and cl (or forces) for a certain 2D airfoil for different angles of attack. The problem is that fluent always gives to big drag and to small lift (compared to experimet). The optimal ratio should be arround 60 but i get only about 10, although the optimum is reached at the same angle of attack. What am I doing wrong. Help please.

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