Consider an airplane modeled after the twin-engine beechcraft queen air executive transport. the airplane has the following characteristics: weight is 38,220 n; wing area is 27.3 m2; aspect ratio is 7.5; oswald efficiency factor is 0.9; and zero-lift drag coefficient cd,0 is 0.03.
1) calculate the thrust required to fly at a velocity of 725 km/h at standard sea level. assume the value of ? ? = 1.225 kg/m3 at standard sea level. (round the final answer to the nearest whole number.) the thrust required to fly at a velocity of 725 km/h at standard sea level is .
2) calculate the thrust required to fly with a velocity of 725 km/h at an altitude of 4.5 km. assume the value of ? ? = 0.777 kg/m3 at an altitude of 4.5 km. (round the final answer to the nearest whole number.) the thrust required to fly with a velocity of 725 km/h at an altitude of 4.5 km is n.

(A) 3052.7 N

(B)13,089.1 N

Explanation:

weight (w) = 38,220 N

wing area (A) = 27.3 m^{2}

Oswald efficiency factor (E) = 0.9

zero-lift drag coefficient (CD0) = 0.03

velocity (v) = 725 km/h = 201.4 m/s

density of air (p) = 1.225 kg/m^{3}

aspect ratio (AR) = 7.5

(A) at standard sea level

  weight (w) =   where Cl = lift coefficient    

Cl = = = 0.5635

coefficient of drag (Cd) = CDO + (take note that π is shown as )

Cd = 0.03 + = 0.045

Cl/Cd = L/D (lift to drag ratio) = 0.5635/0.045 =12.52

Thrust required = w/(l/d) = 38220 / 12.52 = 3052.7 N

(B) At altitude of 4.5 km

density (p) = 0.777 kg/m^{3}

Cl = = = 0.0888

coefficient of drag (Cd) = CDO + (take note that π is shown as )

Cd = 0.03 + = 0.0304

Cl/Cd = L/D (lift to drag ratio) = 0.0888/0.0304 =2.92

Thrust required = w/(l/d) = 38220 / 2.92 = 13,089.1 N

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