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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...
Air flows through a constant area duct. The pressure and temperature of the air at the...
Air flows through a constant area duct. The pressure and temperature of the air at the inlet to the duct are P1 = 100 kPa absolute, and T1 = 298 K, respectively. Inlet Mach number is M1 = 0.1. Heat is transferred to the air as it flows through the duct and as a result the Mach number at the exit increases. a) Find the pressure and temperature at the exit, while the exit Mach number changes between M=0.2 to...
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...
Air enters a compressor operating at steady state at a pressure of 100 kPa, a temperature...
Air enters a compressor operating at steady state at a pressure of 100 kPa, a temperature of 290 K, and with a mass flow rate of 0.72 kg/s. At the exit, the pressure is 700 kPa and the temperature is 450 K. Heat transfer from the compressor to its surroundings occurs at a rate of 3 kW. Kinetic and potential energy changes can be ignored. Determine the power input to the compressor, in kW. Assume that the air is an...
At steady state, air at 200 kPa, 325 K, and mass flow rate of 1.0 kg/s...
At steady state, air at 200 kPa, 325 K, and mass flow rate of 1.0 kg/s enters an insulated duct having differing inlet and exit cross-sectional areas. The inlet cross-sectional area is 6 cm2. At the duct exit, the pressure of the air is 100 kPa and the velocity is 300 m/s. Neglecting potential energy effects and modeling air as an ideal gas, determine a. the velocity of the air at the inlet, in m/s. b. the temperature of the...
V-3. Air flows at steady state through a horizontal, well-insulated, constant-area duct whose diameter is 0.75...
V-3. Air flows at steady state through a horizontal, well-insulated, constant-area duct whose diameter is 0.75 in. At the inlet, p1 = 55.9 lbf/in.2, T1 = 7200R, and the velocity is 9 ft/s. The temperature of the air leaving the duct is 700°R. Determine (a) the velocity at the exit, in ft/s. (b) the pressure at the exit, in lbf/in.2 (c) the magnitude of the net horizontal force exerted by the duct wall on the air, in lbf. In which...
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...
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...
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...
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...
Air enters a compressor operating at steady state at a pressure of 100 kPa, a temperature of 290 K, and with a mass flow rate of 0.72 kg/s. At the exit, the pressure is 700 kPa and the temperature is 450 K. Heat transfer from the compressor to its surroundings occurs at a rate of 3 kW. Kinetic and potential energy changes can be ignored. Determine the power input to the compressor, in kW. Assume that the air is an...
V-3. Air flows at steady state through a horizontal, well-insulated, constant-area duct whose diameter is 0.75 in. At the inlet, p1 = 55.9 lbf/in.2, T1 = 7200R, and the velocity is 9 ft/s. The temperature of the air leaving the duct is 700°R. Determine (a) the velocity at the exit, in ft/s. (b) the pressure at the exit, in lbf/in.2 (c) the magnitude of the net horizontal force exerted by the duct wall on the air, in lbf. In which...
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...
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...
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...
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