Question

**For NACA 23021 ,** By using Thin Airfoil Theory,
mean camber line is y = -0.0231x^{2} + 0.0063x + 0.0153.
Calculate:

a) Zero lift angle of attack
?** _{L}**=?

b) Lift coefficient ?? for ?=−?^{o},?^{o}, and
?^{o}

c) Moment coefficient at quarter chord ??,?/? for
?=−?^{o},?^{o}, and ?^{o}

d) Normalized Center of Pressure ???/? for
?=−?^{o},?^{o}, and ?^{o}

Answer #1

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