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Old   July 18, 2011, 08:52
Default How do you think this will perform?
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I have this sort of aerofoil shaped profile that I am currently testing with ANSYS Fluent to get a plot of lift versus angle attack. I got the results for the lift coefficient at 4 degrees this morning and it seemed a little low at 0.1. The profile is made of a NACA 0030 leading edge with a 440 mm flat section in the middle and a 0035 trailing edge.

A lift coefficient of 0.1 seems too low for a NACA foil but then I started thinking it might be reasonable for a lift coefficient of a flat plate. Do you think this shape would perform like a flat plate and not a NACA foil or am I doing something wrong in Fluent?

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