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January 9, 2006, 08:42 |
TEORIC LIFT Coefficient
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#1 |
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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? THANKS Andy |
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