Question: For the airfoil given in Prob. 4.6, calculate cm c/4 and xcp/c when =3. Data from 4.6 The NACA 4412 airfoil has a mean

For the airfoil given in Prob. 4.6, calculate cm c/4 and xcp/c when α =3°.

Data from 4.6

The NACA 4412 airfoil has a mean camber line given by

|0.25| 0.8 for 0s-s0.4 х [02-03-()] 0.111 0.2+0.8 for 0.4<-s 1


Using thin airfoil theory, calculate

(a) αL=0 (b) c1 when α = 3°.

|0.25| 0.8 for 0s-s0.4 [02-03-()] 0.111 0.2+0.8 for 0.4

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