Question 4(10+10=20 Point): A symmetric airfoil operates at a small angle of attack (alpha =2^circ ) in subsonic flow. The lift coefficient is given by C_(L)=2pi alpha (with a in radians). (a) Calculate the lift coefficient (C_(L)) (b) If the chord length is 1.5 m, wing span is 2 m and the airspeed is 30m/s,rho _(infty )=1.225kg/m^3 determine the lift force.

(a) To calculate the lift coefficient , we need to convert the angle of attack from degrees to radians. Given that the angle of attack is , we can convert it to radians using the formula:Radians = Degrees * (π / 180)So, the angle of attack in radians is:Radians = 2 * (π / 180) = 0.0349 radiansNow, we can calculate the lift coefficient using the given formula: Substituting the value of α in radians, we get: Therefore, the lift coefficient is 0.2196.(b) To determine the lift force, we can use the lift equation: Where:- is the lift force- is the air density- is the airspeed- is the wing area- is the lift coefficientGiven values:- Chord length = 1.5 m- Wing span = 2 m- Airspeed = 30 m/s- Air density = 1.225 kg/m³First, we need to calculate the wing area using the formula: Where:- is the chord length- is the wing spanSubstituting the given values, we get: Now, we can calculate the lift force using the lift equation: $L = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.225 * 900 * 1.5 * 0.2196 = 0.5 * 1.