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I am trying to find the maximum Lift coefficient for airfoil NACA 64A-404. I chose this airfoil for wing. I am stuck at finding the Clmax. I tried to use javafoil but javafoil is showing Cl less than 1 at cruise condition (By putting the Reynolad number value). Although it should be greater than 1? Is there any other method of finding this out?

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