Please help solve these questions. Thank
you.
Also, will the enthalpy increase be 92460 J/kg?
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Please help solve these questions. Thank
you.
Also, will the enthalpy increase be 92460 J/kg?
6...
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...
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...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
Homework Problem IW8 3 Attemps Used 20 Due DateThu, Jul 30, 2020, 23:59:59 Current Time Thu,...
Homework Problem IW8 3 Attemps Used 20 Due DateThu, Jul 30, 2020, 23:59:59 Current Time Thu, Jul 30, 2020, 00:02:48 Air flows through a converging-diverging nozzle/differ. Assuming isentropic flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system Note: The specific heat ratio and gas constant for air are given ask-1A od R-0.287 kg K respectively --Given Vues Inlet Temperature: TI (K) 358 Inlet pressure: PI (kPa) - 626 Inlet Velocity:...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 321 Inlet pressure: P1 (kPa) = 588 Inlet Velocity: V1 (m/s) = 97 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
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...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
Homework Problem IW8 3 Attemps Used 20 Due DateThu, Jul 30, 2020, 23:59:59 Current Time Thu, Jul 30, 2020, 00:02:48 Air flows through a converging-diverging nozzle/differ. Assuming isentropic flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system Note: The specific heat ratio and gas constant for air are given ask-1A od R-0.287 kg K respectively --Given Vues Inlet Temperature: TI (K) 358 Inlet pressure: PI (kPa) - 626 Inlet Velocity:...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
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Please help me with FLOWCHART and UML diagram for class,
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