A small business jet has a wing area of 21.5 m2 and an aspect ratio of 5. Assume

Question

A small business jet has a wing area of 21.5 m2 and an aspect ratio of
5. Assume the wing has a NACA 65-210 airfoil, a span efficiency
factor of 0.9, and a profile drag coefficient of 0.004. Calculate the
wing lift and drag coefficients if the wing is operating at 6 degree
angle-of-attack.

I believe someone answered this question however the second part, "Calculate the
wing lift and drag coefficients if the wing is operating at 6 degree
angle-of-attack" is still unclear. Can someone explain this even further?

Explanation / Answer

To solve the probelm we need the data for Cl. please look to table of NACA 65-210 airfoil in the appendix.Find ao basing basing on the values from the table. this is almost equal to ao = 0.11 / degree Lift slope for a finite wing is given as a = ao / [ 1 + ( 57.3 ao ) / p e R ) ] = 0.11 / [ 1 + (27.3)(0.11) / p (0.9) (5) ] = 0.076/ degree At a = 6 , Coefficient Cl = a (a - aL=0) = Total drag coefficient is C = Cprofile + Cl^2 / p e A R = 0.004 + Cl^2 / p (0.9)(5) plug in values basing on the data from the tables.

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