An aircraft gross weight at takeoff is 56,000 pounds and has Wing planform area 900ft2 wing...

 

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An aircraft gross weight at takeoff is 56,000 pounds and has Wing planform area 900ft2 wing span of 90. The plane has a turbojet engine with a thrust at sea level of 1,202 lb and a specific fuel consumption of 1.3 lb/(lb.h). Fuel capacity: 550 gal. Its drag polar equation is given by CD = 0.016 + 0.04CL2. The maximum value of C_L/C_D The maximum value of (C_L^(1/2))/C_D The velocities at which they occur at sea level The velocities at which they occur at 10,000 ft Find the minimum thrust required for straight and level flight and the corresponding true airspeeds at sea level and at 30,000 ft. Find minimum power required and the corresponding airspeeds at sea level and 30,000 ft An aircraft gross weight at takeoff is 56,000 pounds and has Wing planform area 900ft2 wing span of 90. The plane has a turbojet engine with a thrust at sea level of 1,202 lb and a specific fuel consumption of 1.3 lb/(lb.h). Fuel capacity: 550 gal. Its drag polar equation is given by CD = 0.016 + 0.04CL2. The maximum value of C_L/C_D The maximum value of (C_L^(1/2))/C_D The velocities at which they occur at sea level The velocities at which they occur at 10,000 ft Find the minimum thrust required for straight and level flight and the corresponding true airspeeds at sea level and at 30,000 ft. Find minimum power required and the corresponding airspeeds at sea level and 30,000 ft