a subsonic flow enters a 1-D duct that is frictionless. the inlet stagnation temperature is 250K....
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subsonic flow enters a 1-D duct that is frictionless. the inlet
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1. A subsonic (M) fow of nitrogen with stagnation temperature T, and stagnation pressure p, values...
1. A subsonic (M) fow of nitrogen with stagnation temperature T, and stagnation pressure p, values of 1050°R and 100 psia respectively enters a device with a cross-sectional inlet area4 .1.Assume that there is no heat transfer, work interaction as the gas passes through the device and expands to 14.7 psia (a) Compute p,V/, and 10 (b) Compute M,,V,, and p, 144c
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. A...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
1. Airflow enters a duct at a total pressure of 250 kPa and a total temperature...
1. Airflow enters a duct at a total pressure of 250 kPa and a total temperature of 350 K. The inlet static pressure, P, is 239.35 kPa. The flow exits a converging section at 2 where the area is 0.01 m2. Treat air as an ideal gas where k 14. Pback- 120kpa (a) Determine the Mach number at A2 (b) Determine the exit static pressure and temperature at 2. (c) Determine the mass flow rate. (d) Determine the inlet area...
Flow enters the combustor of a jet engine at a Mach number of 0.5, a temperature...
Flow enters the combustor of a jet engine at a Mach number of 0.5, a temperature of 390K and a pressure of 200kPa. (a) Determine the maximum amount of heat that can be added to this flow, assuming that the combustion chamber has the form of a constant area duct, and the properties of the air/fuel mixture flowing through the combustor are the same as those of air. (b) The flow entering the combustor 1 has a fuel to air...
2.-Consider a cylindrical combustion chamber where air enters at 480 kPa with a density of 3.05...
2.-Consider a cylindrical combustion chamber where air enters at 480 kPa with a density of 3.05 kg/m. At inlet the stagnation air temperature is 553K. Heat is added by combustion and the air exits the chamber at a Mach number of 0.4. Determine the stagnation temperature at the exit and the specific heat added to the chamber due to combustion if the chamber is assumed frictionless. Specific heat at constant pressure of air is 1.005 kJ/kg.K and the gas constant...
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging...
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging nozzle. The throat area of the nozzle is 5 cm2, the exit area is 12.5 cm2. The back pressure is 350 kPa and a normal shock occurs within a diverging section. Determine (a) exit Mach number, (b) change in stagnation pressure, (c) upstream and downstream Mach number of shock (d) cross sectional area where shock occurs (e) back pressure if the flow were isentropic...
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...
)An axial-flow turbine operating with an overall stagnation pressure of 8to 1 has a polytropic efficiency...
)An axial-flow turbine operating with an overall stagnation pressure of 8to 1 has a polytropic efficiency of 0.85. Determine the total-to-total efficiency of the turbine.b)If the exhaust Mach number of the turbine is 0.3, determine the total-to-static efficiency.c)If, in addition, the exhaust velocity of the turbine is 160 m/s, determine the inlet total temperature.Assume for the gas that Cp=1.175 kJ/(kg K) and R=287 kJ/(kg K).
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by...
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by a large compress-air tank with pressure of 700 kPa and temperature of 540 K. The flow is shockless everywhere and is supersonic at the nozzle exit. Between section 1 and 2, heat added into the duct at a rate of 100.4 kJ/(kg of air). Assuming frictionless flow and ideal gas. Find these properties at section 2: M2. P2.T2 and Poz. 1, nozzle exit Po...
Question 4 (16 Marks) A frictionless, adiabatic compressor compresses hydrogen at a pressure of 3 bar and a temperat...
Question 4 (16 Marks) A frictionless, adiabatic compressor compresses hydrogen at a pressure of 3 bar and a temperature of 10 °C, to a pressure of 16 bar. The hydrogen enters the compressor at a velocity of 80 m/s and exits at negligible velocity. From the compressor, the hydrogen is passed at constant pressure through a duct and cooled to a temperature of 55 °C, in the process. The hydrogen mass flow rate is 0.5 kg/s, and all changes in...
1. A subsonic (M) fow of nitrogen with stagnation temperature T, and stagnation pressure p, values of 1050°R and 100 psia respectively enters a device with a cross-sectional inlet area4 .1.Assume that there is no heat transfer, work interaction as the gas passes through the device and expands to 14.7 psia (a) Compute p,V/, and 10 (b) Compute M,,V,, and p, 144c
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
1. Airflow enters a duct at a total pressure of 250 kPa and a total temperature of 350 K. The inlet static pressure, P, is 239.35 kPa. The flow exits a converging section at 2 where the area is 0.01 m2. Treat air as an ideal gas where k 14. Pback- 120kpa (a) Determine the Mach number at A2 (b) Determine the exit static pressure and temperature at 2. (c) Determine the mass flow rate. (d) Determine the inlet area...
2.-Consider a cylindrical combustion chamber where air enters at 480 kPa with a density of 3.05 kg/m. At inlet the stagnation air temperature is 553K. Heat is added by combustion and the air exits the chamber at a Mach number of 0.4. Determine the stagnation temperature at the exit and the specific heat added to the chamber due to combustion if the chamber is assumed frictionless. Specific heat at constant pressure of air is 1.005 kJ/kg.K and the gas constant...
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...
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by a large compress-air tank with pressure of 700 kPa and temperature of 540 K. The flow is shockless everywhere and is supersonic at the nozzle exit. Between section 1 and 2, heat added into the duct at a rate of 100.4 kJ/(kg of air). Assuming frictionless flow and ideal gas. Find these properties at section 2: M2. P2.T2 and Poz. 1, nozzle exit Po...
Question 4 (16 Marks) A frictionless, adiabatic compressor compresses hydrogen at a pressure of 3 bar and a temperature of 10 °C, to a pressure of 16 bar. The hydrogen enters the compressor at a velocity of 80 m/s and exits at negligible velocity. From the compressor, the hydrogen is passed at constant pressure through a duct and cooled to a temperature of 55 °C, in the process. The hydrogen mass flow rate is 0.5 kg/s, and all changes in...
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