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CL and CD reference values

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Old   March 31, 2015, 14:43
Default CL and CD reference values
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Hello

I am simulating the flow over a 2 element airfoil which is to say that there is a main wing and a flap. I want all coefficients to be scaled to a unit chord. I am unsure whether FLUENT uses the real length of the airfoil or the reference length.

In other words if my reference length is set to 1m then will CL and CD be calculated assuming a chord length of 1m even though the main wing and flap have chords less than 1m?

Thanks in advance for the help.
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Old   March 31, 2015, 18:41
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This question has already been answered by Jason back in 2005.
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drag coefficient, lift and drag, lift coefficient, reference -values

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