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(a) A high speed (Mach number > 0.3) aircraft is flying at an altitude where the...
. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m,...
. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m, where the ambient conditions are 50 kPa and -12°C (a negative value). The pressure ratio across the compressor is 13, and the turbine inlet temperature (TIT) is 1330 K. Assuming ideal operation for all components and constant specific heats for the air at room temperature (cold air model). (a) Sketch the T-s diagram of the cycle, and determine: (b) The Mach number of the...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat pl...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear a) supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data Total Wing Area: 18.22 m Aircraft Mass: 8,000 kg Is supersonic linear theory valid for this flight regime? Explain...
Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear supersonic theor...
Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data: • Total Wing Area: 18.22 m2 • Aircraft Mass: 8,000 kg -Is supersonic linear theory valid for this flight regime? Explain your answer.
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft flies with a velocity of 289 m/s at an altitude where the air is at a pressure of 29.5 kPa and temperature of-31.0·C. The air enters the compressor at 54 kg/s. The fuel used during the flight is rated to provide 39300 kJ of heat energy from every kilogram burnt and the temperature of the air entering the turbine is 1047.744 K. Calculate...
Consider a turbofan engine with a bypass ratio of 6. The cruising Mach number is 0.85...
Consider a turbofan engine with a bypass ratio of 6. The cruising Mach number is 0.85 at an altitude of 12000 m with an ambient temperature of 217 K. The ratio of stagnation pressure and ambient pressure for the fan and the core engine is 1.6. The stagnation temperature is 600 K at the exit of the core engine and 340 K at the exit of the fan. (a) If the fan and core streams expand in separate nozzles to...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air...
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at Mach Number of 0.8. The gas constant and specific heat ratio of air are 0.287 kJ/kg k, 1.4 respectively. Determine, (1) air velocity: (11) stagnation pressure: (111) stagnation temperature and (iv) stagnation density (8 marks) Nitrogen enters a converging diverging nozzle from a reservoir at a pressure of 700 kPa...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000 ft) where the engine entrance temperature is 228 K and the pressure is 30.8 kPa. We also know that the engine compressor pressure ratio is rp= 10 and the fuel to air mass flowrate ratio is 0.03. If the aircraft is moving at a velocity of 305 m/s and uses fuel with LHV 44,102 kJ/kg calculate the engine exhaust velocity. (Note that cp 1.0035...
Please show full steps, will rate. A turbojet powered aircraft is flying at 250 m/s where...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear a) supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data Total Wing Area: 18.22 m Aircraft Mass: 8,000 kg Is supersonic linear theory valid for this flight regime? Explain...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft flies with a velocity of 289 m/s at an altitude where the air is at a pressure of 29.5 kPa and temperature of-31.0·C. The air enters the compressor at 54 kg/s. The fuel used during the flight is rated to provide 39300 kJ of heat energy from every kilogram burnt and the temperature of the air entering the turbine is 1047.744 K. Calculate...
Consider a turbofan engine with a bypass ratio of 6. The cruising Mach number is 0.85 at an altitude of 12000 m with an ambient temperature of 217 K. The ratio of stagnation pressure and ambient pressure for the fan and the core engine is 1.6. The stagnation temperature is 600 K at the exit of the core engine and 340 K at the exit of the fan. (a) If the fan and core streams expand in separate nozzles to...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at Mach Number of 0.8. The gas constant and specific heat ratio of air are 0.287 kJ/kg k, 1.4 respectively. Determine, (1) air velocity: (11) stagnation pressure: (111) stagnation temperature and (iv) stagnation density (8 marks) Nitrogen enters a converging diverging nozzle from a reservoir at a pressure of 700 kPa...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000 ft) where the engine entrance temperature is 228 K and the pressure is 30.8 kPa. We also know that the engine compressor pressure ratio is rp= 10 and the fuel to air mass flowrate ratio is 0.03. If the aircraft is moving at a velocity of 305 m/s and uses fuel with LHV 44,102 kJ/kg calculate the engine exhaust velocity. (Note that cp 1.0035...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
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