Question 2 (10+10=20 Points): An airfoil with a chord length of 1.5 m is in a flow with V_(infty )=50m/s and rho =1.2kg/m^3 The airfoil is cambered and has a zero-lift angle of attack of alpha _(L=0)=-1^circ (a) Calculate the lift coefficient at alpha =5^circ . (b) Determine the total lift force per unit span acting on the airfoil.

(a) To calculate the lift coefficient at , we can use the lift coefficient equation for a cambered airfoil: where: is the lift coefficient, is the air density, is the free stream velocity, is the half-chord length, is the chord length, is the angle of attack, and is the zero-lift angle of attack.Given: Substituting the given values into the equation: $C_L = \frac{2 \pi \times 1.2 \times