Problem 6.02: An airplane powered by a single JT4A-3 turbo jet engine has a maximum cruising...
Problem 6.02: An airplane powered by a single JT4A-3 turbo jet engine has a maximum cruising speed of 500kt at a standard altitude of 6000m. What’s the airplane’s drag in Newtons and at what rate is fuel being expanded?
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Problem 6.02: An airplane powered by a single JT4A-3 turbo jet
engine has a maximum cruising...
Problem 2.2_(AE12.5_Flight_Mechanics) A jet-powered airplane attempts to maximize its range using a constant lift coefficient and...
Problem 2.2_(AE12.5_Flight_Mechanics) A jet-powered airplane attempts to maximize its range using a constant lift coefficient and constant airspeed flight profile. (a) Estimate the maximum range that the jet could achieve assuming the flight begins at sea level on a standard day. (b) What is the airplane's altitude at the end of the flight? initial weight, 12,000 lbt final weight, Wf - 8,000 lbf wing reference area, S-300 ft induced drag factor, K0.073 zero-lift drag coefficient, cDo 0.023 2
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N...
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N General • Fuel weight = 50000 N Wing 2 Wing area = 50 m Wing aspect ratio (AR) = 6.5 Wing span efficiency factor (e) = 0.87 Aerodynamics . = MARE • Zero-lift drag coefficient = 0.032 Drag Cp = Cpo + kc where k = kı + kz kı = 0 and k3 Lift CLmax = 1.4 during flight Two turbojet engines. (thrust...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the dens...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
Boeing 767-400ER model airplane has two engines. Each engine can have a maximum thrust (mechanical force)...
Boeing 767-400ER model airplane has two engines. Each engine can have a maximum thrust (mechanical force) output of 270 kN. When the plane is cruising at 749.77 km/h, the pilot decides to increase the speed to the typical 850.0 km/h. If drag on the plane is on average 25556 N, and the engines are engaged at 35.21 % of their maximum thrust output, and the plane weighs 128256 kg, how long does it take to reach the new cruising speed?...
Boeing 767-400ER model airplane has two engines. Each engine can have a maximum thrust (mechanical force)...
Boeing 767-400ER model airplane has two engines. Each engine can have a maximum thrust (mechanical force) output of 270 kN. When the plane is cruising at 739.64 km/h, the pilot decides to increase the speed to the typical 850.0 km/h. If drag on the plane is on average 28657 N, and the engines are engaged at 35.84% of their maximum thrust output, and the plane weighs 156892 kg, how long does it take to reach the new cruising speed? Include...
Problem III A small airplane has a total mass of 1800 kg and a wing area...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
When its 115-kW (154.1-hp) engine is generating full power, a small single-engine airplane with mass 685...
When its 115-kW (154.1-hp) engine is generating full power, a small single-engine airplane with mass 685 kg gains altitude at a rate of 3.0 m/s (180 m/min, or 590.4 ft/min). What fraction of the engine power is being used to make the airplane climb? (The remainder is used to overcome the effects of air resistance and of inefficiencies in the propeller and engine.)
Constants Part A When its engine of power 70 kW is generating full power, a small single-engine airplane with mass 670 kg gains altitude at a rate of 2.4 m/s What fraction of the engine power is bein...
Constants Part A When its engine of power 70 kW is generating full power, a small single-engine airplane with mass 670 kg gains altitude at a rate of 2.4 m/s What fraction of the engine power is being used to make the airplane climb? (The remainder is used to overcome the effects of air resistance and of inefficiencies in the propeller and engine.) Express your answer as a percentage using two significant figures 215 Submit X Incorrect: Try Again; 4...
A jet airplane in level flight has a mass of 8.62 ✕ 104 kg, and the...
A jet airplane in level flight has a mass of 8.62 ✕ 104 kg, and the two wings have an estimated total area of 95.0 m2. (a) What is the pressure difference between the lower and upper surfaces of the wings? Pa (b) If the speed of air under the wings is 229 m/s, what is the speed of the air over the wings? Assume air has a density of 1.29 kg/m3. m/s (c) Explain why all aircraft have a...
A jet airplane in level flight has a mass of 8.61 x 104 kg, and the...
A jet airplane in level flight has a mass of 8.61 x 104 kg, and the two wings have an estimated total area of 88.0 m2 (a) What is the pressure difference between the lower and upper surfaces of the wings? Pa (b) If the speed of air under the wings is 233 m/s, what is the speed of the air over the wings? Assume air has a density of 1.29 kg/m3 m/s (c) Explain why all aircraft have a...
Problem 2.2_(AE12.5_Flight_Mechanics) A jet-powered airplane attempts to maximize its range using a constant lift coefficient and constant airspeed flight profile. (a) Estimate the maximum range that the jet could achieve assuming the flight begins at sea level on a standard day. (b) What is the airplane's altitude at the end of the flight? initial weight, 12,000 lbt final weight, Wf - 8,000 lbf wing reference area, S-300 ft induced drag factor, K0.073 zero-lift drag coefficient, cDo 0.023 2
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N General • Fuel weight = 50000 N Wing 2 Wing area = 50 m Wing aspect ratio (AR) = 6.5 Wing span efficiency factor (e) = 0.87 Aerodynamics . = MARE • Zero-lift drag coefficient = 0.032 Drag Cp = Cpo + kc where k = kı + kz kı = 0 and k3 Lift CLmax = 1.4 during flight Two turbojet engines. (thrust...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
Boeing 767-400ER model airplane has two engines. Each engine can have a maximum thrust (mechanical force) output of 270 kN. When the plane is cruising at 739.64 km/h, the pilot decides to increase the speed to the typical 850.0 km/h. If drag on the plane is on average 28657 N, and the engines are engaged at 35.84% of their maximum thrust output, and the plane weighs 156892 kg, how long does it take to reach the new cruising speed? Include...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
Constants Part A When its engine of power 70 kW is generating full power, a small single-engine airplane with mass 670 kg gains altitude at a rate of 2.4 m/s What fraction of the engine power is being used to make the airplane climb? (The remainder is used to overcome the effects of air resistance and of inefficiencies in the propeller and engine.) Express your answer as a percentage using two significant figures 215 Submit X Incorrect: Try Again; 4...
A jet airplane in level flight has a mass of 8.61 x 104 kg, and the two wings have an estimated total area of 88.0 m2 (a) What is the pressure difference between the lower and upper surfaces of the wings? Pa (b) If the speed of air under the wings is 233 m/s, what is the speed of the air over the wings? Assume air has a density of 1.29 kg/m3 m/s (c) Explain why all aircraft have a...
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