Consider an airplane patterned after the Beechcraft Bonanza V-tailed, single-engine light private airplane, whose characteristics are...

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Consider an airplane patterned after the Beechcraft Bonanza V-tailed, single-engine light private airplane, whose characteristics are as follows. Wing geometry: AR= 6.2. S= 16.82 m² Normal gross weight: W₁ = 14,324 N Parasite drag coefficient: Cp = 0.027 Oswald efficiency factor: e = 0.91 Power plant: Single piston engine with Pmax=257.27 x 10³ Watt at sea level, and n = 0.83 for the two-blade propeller Specific fuel consumption: c= 6.959 x 10-7 N/(W-s) Fuel weight: W, 1,104 N 2.1 [2 points] Estimate the sea-level liftoff distance, assuming a paved runway with the friction coefficient during take-off PLO= 0.02 and the maximum lift coefficient during the ground roll is 1.1. When the airplane is on the ground, the wings are 1.22m above the ground. Note that (PA)max = 1Pmax = Tmax Voo for a propeller-driven airplane. ( 2.2 [2 points] estimate the sea-level landing ground roll distance, assuming that the fuel is almost fully used up before landing (i.c., empty weight) and the maximum lift coefficient with flaps at touchdown is 1.8. After touchdown, assume zero lift and off μ = 0.4. Finally, when a thrust reversal device and parachutes are utilized to reduce the landing distance, determine the minimum sum of thrust reversal and additional drag required to have the sea-level landing distance less than 120m. Consider an airplane patterned after the Beechcraft Bonanza V-tailed, single-engine light private airplane, whose characteristics are as follows. Wing geometry: AR= 6.2. S= 16.82 m² Normal gross weight: W₁ = 14,324 N Parasite drag coefficient: Cp = 0.027 Oswald efficiency factor: e = 0.91 Power plant: Single piston engine with Pmax=257.27 x 10³ Watt at sea level, and n = 0.83 for the two-blade propeller Specific fuel consumption: c= 6.959 x 10-7 N/(W-s) Fuel weight: W, 1,104 N 2.1 [2 points] Estimate the sea-level liftoff distance, assuming a paved runway with the friction coefficient during take-off PLO= 0.02 and the maximum lift coefficient during the ground roll is 1.1. When the airplane is on the ground, the wings are 1.22m above the ground. Note that (PA)max = 1Pmax = Tmax Voo for a propeller-driven airplane. ( 2.2 [2 points] estimate the sea-level landing ground roll distance, assuming that the fuel is almost fully used up before landing (i.c., empty weight) and the maximum lift coefficient with flaps at touchdown is 1.8. After touchdown, assume zero lift and off μ = 0.4. Finally, when a thrust reversal device and parachutes are utilized to reduce the landing distance, determine the minimum sum of thrust reversal and additional drag required to have the sea-level landing distance less than 120m.