Consider the wing given below & assume zero geom. twist distribution. The wing's following geometric parameters are:

Span $=b=100ft$

Reference $($platform$)$ area $=S=1500f{t}^2$

Sweep of $\frac{1}{2}$ chord line $==10$ deg.

Airfoil section lift slope $=a_0=\frac{0\mathrm{.}10}{d}eg$

Airfoil Zero$-$lift angle of attack $=a_{o{L}_{2}D}=-2$deg

Estimate for this wing of incompressible conditions: $(25$ pts$)$

a$.$ Aspect ratio

b$.$ Span efficiency

c$.$ Zero$-$lift angle of attack

d$.$ Lift curve slope, $C_{L_{}}$

e$.$ Plot CL vs angle of attack and CL vs CD

f$.C_{D_i}($ie$,$ lift induce drag coeff.$)$ at $=5$deg

g$.$ The spanwise location where non$-$linear flow separation will first appear as angle of attack is increased.

h$.$ For this same wing $-$ Estimate the $C_L$ at $=5$deg for a condition of $M=0\mathrm{.}75.$