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For NACA 23021 , By using Thin Airfoil Theory, mean camber line is y = -0.0231x2...

For NACA 23021 , By using Thin Airfoil Theory, mean camber line is y = -0.0231x2 + 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

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