A Turbojet-engined aircraft flies at 350m/s at an altitude of 9000 m. The pressure at this...

A Turbojet-engined aircraft flies at 350m/s at an altitude of 9000 m. The pressure at this height is 30 kPa and the temperature is-32⁰ C. The pressure ratio of the compressor is 12, the turbine input temperature is 1400 K. Air enters the compressor with a flow of 60 kg/s and the heat value of the fuel is 42 700 kJ/kg. Admitting that adiabatic efficiency of compressor, turbine and Lule is 100% and specific temperatures are constant at room temperature,
a) The speed at which the combustion end gases exit the engine,
b) Reaction force,
c) Calculate the amount of fuel consumed in Unit time. (k=1.4 Cp=1.005 kj/kgK )

Solutions

Expert Solution

samet mamat answered 1 year ago

Next > < Previous

Related Solutions

At an altitude where the air is at 35 kPa and -40°C a turbojet aircraft flies...

At an altitude where the air is at 35 kPa and -40°C a turbojet aircraft flies with a velocity of 260 m/s. Compressor has a pressure ratio of 10, and the temperature of the gases at the turbine inlet is 1100°C. Air enters the compressor at a rate of 45 kg/s. *Part(A)* Use *hot air standard assumptions* to find (a) the temperature and pressure of the gases at the turbine exit (b) the velocity of the gases at the nozzle...

Prob.3) A jet-powered aircraft flies at a speed of 320 m / s at an altitude...

Prob.3) A jet-powered aircraft flies at a speed of 320 m / s at an altitude of 9150 m, where the ambient conditions are 32 kPa and –32 ° C. The pressure ratio in the compressor is 12 and the temperature at the inlet of the turbine is 1,400 K. The air enters the compressor at a rate of 60 kg / s and the jet fuel has a calorific value of 42,700 kJ / kg. Assuming ideal operation for...

A jet engine flies at 205 m/s at an altitude where the pressure is 0.466atm and...

A jet engine flies at 205 m/s at an altitude where the pressure is 0.466atm and the temp is 249K. The pressure recovery factor across the intake is 1.0 and the compressor pressure ratio is 30. Assume isentropic turbomachinery. A) determine flight mach number B) determine stagnation pressure and temp at the inlet of the intake C) determine the stagnation pressure and temp after the compeessor D) determine the stagnation temp change across the turbine drivibg the compressor

Summarize how a pressure altimeter works to determine and display aircraft altitude and explain the meaning...

Summarize how a pressure altimeter works to determine and display aircraft altitude and explain the meaning of the saying in aviation, “high to low, or hot to cold, look out below.” Give an example of an aircraft incident related to pressure altimeter error.

Prob. 2) A jet powered aircraft flies at a speed of 900 ft / s at...

Prob. 2) A jet powered aircraft flies at a speed of 900 ft / s at an altitude of 20,000 ft, where the ambient conditions are 7 psia and 10 ° F. The pressure ratio in the compressor is 13 and the temperature at the inlet of the turbine is 2400 R. Assuming an ideal operation for all specific components and heats constants for air at room temperature draw and graph the physical and T-S diagrams and determine: a) the...

What is the maximum angle of climb (steady velocity climb) for a turbojet powered aircraft with...

What is the maximum angle of climb (steady velocity climb) for a turbojet powered aircraft with an (L?D)max equal to 10.5 and a gross weight of 8000 lb. if it is producing a thrust of 2000 lb.? If the aircraft using the same available thrust, wishes to establish a rate of climb equal to 1800fpm, what airspeed will it need to establish? (Assume the required thrust equals 764pounds)

A 1300 kg aircraft going 35 m/s collides with a 1500 kg aircraft that is parked...

A 1300 kg aircraft going 35 m/s collides with a 1500 kg aircraft that is parked and they stick together after the collision and are going 16.3 m/s after the collision. If they skid for 14.3 seconds before stopping, how far did they skid? Hint: Are the aircraft moving at a constant velocity after the collision or do they experience an acceleration?

Consider and airplane flying at a pressure altitude of 40,000 feet and a density altitude of...

Consider and airplane flying at a pressure altitude of 40,000 feet and a density altitude of 30,000 feet. Calculate the outside air temperature.

FLUID MECHANICS An aircraft flying at an altitude of 5 km with a Mach number of...

FLUID MECHANICS An aircraft flying at an altitude of 5 km with a Mach number of 0.15. Calculate the velocity of the aircraft? (+1 point) Calculate the pitot tube measurement reading at the nose using Bernoulli (+1 point) and Isentropic equations (+1 point) separately. Compare them!!! Calculate pressure coefficient (Cp) at the nose(stagnation) point. (+0.5 point) Calculate the pressure coefficient (Cp) at the point where Mach number reaches 0.25 (+1 point)

a. Why are commercial or any aircraft that fly at altitude, pressurized? b. What is Pascal’s...

a. Why are commercial or any aircraft that fly at altitude, pressurized? b. What is Pascal’s pressure assumption? c. What are typical pressures used within commercial aircraft? d. Explain air pressure and why it is higher at sea level than at high altitudes, support with diagrams if needed. (Hint, in a room is the cold air, it is at the floor. Is its density greater than hot air?)

Subjects