Estimate required maximum camber as a percentage of chord

Reference no: EM131515197

Question: Use thin-airfoil theory to select a NACA four-digit wing section with a coef- ficient of lift at zero incidence approximately equal to unity. The maximum camber must be located at 40% chord and the thickness ratio is to be 0.10. Estimate the required maximum camber as a percentage of chord to the nearest whole number.

Reference no: EM131515197

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