Estimate the required maximum camber

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Reference no: EM131515215

Question: Use thin-airfoil theory to select a NACA four-digit wing section with a coefficient of lift at zero incidence approximately equal to unity and a pitchingmoment coefficient C_M1/4 = -0.025. The thickness ratio is to be 0.10. Estimate the required maximum camber as a percentage of chord to the nearest whole number and its position to the nearest tenth of a chord. The CL value must be within 1% of the required value and C_M1/4 within 3%.

Reference no: EM131515215

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