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

Question

Answer 1

(a) To calculate the lift coefficient at

, we can use the lift coefficient equation for a cambered airfoil:

where

is the lift coefficient and

is the angle of attack in radians.First, we need to convert the angle of attack from degrees to radians:

Now, we can substitute the value of

into the lift coefficient equation:

$C_L = \frac

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