(Solved): Consider the above aircraft in a straight, level and unaccelerated fight. Suppose the aircraft has ...

Consider the above aircraft in a straight, level and unaccelerated fight. Suppose the aircraft has a wing planform area (S) of \( 1.370 \) ft \( { }^{2} \) and is traveling at a velocity (V) of \( 540 \mathrm{ft} / 5 \). If the aircraft is at sea level with an air density \( (p) \) of \( 0.002377 \) slug/ft , and a lift coefficient \( \left\{C_{l}\right) \) of \( 0.375 \), calculate the weight \( (W) \) of the aircraft: 5. Assume the aircraft from the above problem is climbing with an angle of attack of \( 10^{\circ} \). Using the weight of the aircraft from problem 5 , calculate the lift force of the aircraft. Additionally, calculate the climb rate (Vcumat of the aircraft. 6. Using the lift and the weight of the aircraft from problem 5 , calculate the load factor \( (n) \) of the aircraft.