Question 4 (15 Points): Consider a light, single -engine, propeller-driven airplane The airplane weight is 1470 kg and the wing reference area is 16m^2 Assume a steady level flight at sea level.where the ambient atmospheric density is 1.225kg/m^3 The drag coefficient of the airplane C_(D) is a function of the lift coefficient C_(L) ; this function for the given airplane is C_(D)=0.025+0.054C_(L^2)^2 For two flight velocities of V=40m/s calculate C_(L) and C_(D) coefficients.

To calculate the lift coefficient ( ) and drag coefficient ( ) for the given airplane at a velocity of , we need to use the relationship between lift force, drag force, and weight of the airplane. First, let's calculate the lift force ( ) required for steady level flight. The lift force must balance the weight of the airplane: where is the weight of the airplane. Given that the weight of the airplane is and assuming the acceleration due to gravity is , we have: Next, we use the lift equation to find the lift coefficient. The lift force is also given by: where is the ambient atmospheric density, is the velocity, and is the wing reference area. Rearranging this equation to solve for , we get: Substituting the given values, we have: Now that we have the lift coefficient, we can calculate the drag coefficient using the given relationship: Substituting the value of we found: Therefore, for a velocity of , the lift coefficient ( ) is approximately and the drag coefficient ( ) is approximately .