Question

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. So 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) = 8.81 Throat area: A (cm^2) = 5.05 Area at diffuser exit: A (cm^2) = 7.19 a) Determine the Mach number at the inlet. Your Answer = 326 Correct! Exact Answer=0.3263 +/- 9.4E-04 b) Determine the stagnation temperature (K) at the inlet. Your Answer = 355.396 Correct! Exact Answer=355.41 +/- 1.4E+00 c) Determine the stagnation pressure (kPa) at the inlet. Your Answer = 585.556 Correct! Exact Answer= 585.62 +/- 2.4E+00 d) Determine the theoretical throat area (cm^2) for sonic flow (A*). Your Answer = 4.659 Correct! Exact Answer= 4.663 +/- 1.2E-02 e) Determine the Mach number at the throat. Your Answer = Incorrect. 1) Determine the temperature (K) at the throat. Your Answer = Incorrect. g) Determine the velocity (m/s) at the throat. Your Answer = h) Determine the pressure (kPa) at the throat. Your Answer = i) Determine the mass flow rate (kg/s) through the nozzle Your Answer = 1) Determine the Mach number at the exit. Your Answer = k Determine the temperature. ( Kat the exit

Answer 1

Solution:

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