Consider a converging-diverging nozzle with subsonic inlet conditions. Answer with justification. Use the sketch of the...
Consider a converging-diverging nozzle with subsonic inlet conditions. Answer with justification. Use the sketch of the pressure diagram wherever appropriate. Gamma = 1.4. R = 286.9 J/kg-K
It is given that when the exit pressure is 1MPa, a certain nozzle is operating under choked, subsonic and isentropic conditions. The mass flow rate is found to be 1000 kg/s. What will be the mass flow rate if the exit pressure is 100 kPa? Explain.
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Consider a converging-diverging nozzle with subsonic inlet
conditions. Answer with justification. Use the sketch of the...
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...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions...
Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions at the throat of the converging-diverging nozzle? (circle all correct answers and assume friction is negligible in the nozzle). a. Subsonic flowb. Supersonic flowc. Sonic flow
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. (5 pts.) Assume air is entering a converging-diverging nozzle with subsonic speed. What are the...
2. (5 pts.) Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions at the throat of the converging-diverging nozzle? (circle all correct answers and assume friction is negligible in the nozzle). a. Subsonic flow b. Supersonic flow C. Sonic flow
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-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...
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) =...
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...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
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. (5 pts.) Assume air is entering a converging-diverging nozzle with subsonic speed. What are the possible flow conditions at the throat of the converging-diverging nozzle? (circle all correct answers and assume friction is negligible in the nozzle). a. Subsonic flow b. Supersonic flow C. Sonic flow
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-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...
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...
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