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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) = 336Inlet pressure: P1 (kPa) = 581Inlet Velocity: V1 (m/s) = 86Area at nozzle inlet: A1 (cm^2) = 8.19Throat area: A (cm^2) = 3.69Area at diffuser exit: A (cm^2) = 6.66(a) Determine the theoretical throat area (cm^2) for sonic flow (A).(b) Determine the Mach number at the throat.(c) Determine the temperature (K) at the throat.(d) Determine the velocity (m/s) at the throat.(e) Determine the pressure (kPa) at the throat.(f) Determine the mass flow rate (kg/s) through the nozzle.

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Answer:

See solution

Explanation:

-Given Values-

Inlet Temperature: T1 (K) = 320

Inlet pressure: P1 (kPa) = 650

Inlet Velocity: V1 (m/s) = 129

Area at nozzle inlet: A1 (cm^2) = 7.11

Throat area: A (cm^2) = 4.53

Area at diffuser exit: A (cm^2) = 6.39

Need Help Solving e-l please.

e) Determine the Mach number at the throat.

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f) Determine the temperature (K) at the throat.

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g) Determine the velocity (m/s) at the throat.

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h) Determine the pressure (kPa) at the throat.

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i) Determine the mass flow rate (kg/s) through the nozzle

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j) Determine the Mach number at the exit.

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k) Determine the temperature (K) at the exit.

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l) Determine the velocity (m/s) at the exit.

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