Calculate the wing zero-lift angle of attack

Reference no: EM13254023

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.

Reference no: EM13254023

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