A tapered, swept wing is constructed using a uniform NACA 4412 airfoil section. The wing has a total wingspan of b = 36 m. The root of the wing has a chord length of c(0) = 7 m, and the tip of the wing has a chord length of c(b/2) = 1.5 m. The leading edge has a sweep angle of 25 degrees. The twist angle is degrees.
1. Calculate the wing surface area S, aspect ratio A, and mid-chord sweep angle %u039Bc/2.
2. Using the approximation discussed in class, calculate the wing lift effectiveness CL%u03B1
3. Calculate the wing zero-lift angle of attack.
4. Calculate the location Xac of the wing%u2019s aerodynamic center.
5. Calculate the wing pitch moment coefficient CMac about its aerodynamic center.