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ANSWER [0.54 and 1.63] (b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to b...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet sta...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
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...
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-0287 kJ/kg-K respectively --Given Values-- Inlet Temperature: TI (K) 349 Inlet pressure: Pl (kPa) 460 Inlet Velocity: V1 (m/s) 73 Area at nozzle inlet: Al (cmA2) 8.19 Throat area: A...
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. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throa...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throa...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
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 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) =...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
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-0287 kJ/kg-K respectively --Given Values-- Inlet Temperature: TI (K) 349 Inlet pressure: Pl (kPa) 460 Inlet Velocity: V1 (m/s) 73 Area at nozzle inlet: Al (cmA2) 8.19 Throat area: A...
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. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
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 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) =...
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