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TEORIC LIFT Coefficient

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Old   January 9, 2006, 09:42
Default TEORIC LIFT Coefficient
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Teoric Lift coeff for thin aerofoil with AR=4 AOA(&alpha=15 degree --> 0.261 radianti

for me is 1.09

calculate with mathematical law

CL= 2πα / (1+2/AR) where α is in radianti

Is it correct for you?


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