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) = 352
Inlet pressure: P1 (kPa) = 639
Inlet Velocity: V1 (m/s) = 86
Area at nozzle inlet: A1 (cm^2) = 5.59
Throat area: A (cm^2) = 2.29
Area at diffuser exit: A (cm^2) = 2.98
a) Determine the Mach number at the inlet.
b) Determine the stagnation temperature (K) at the inlet.
c) Determine the stagnation pressure (kPa) at the inlet.
d) Determine the theoretical throat area (cm^2) for sonic flow (A*).
e) Determine the Mach number at the throat.
f) Determine the temperature (K) at the throat.
g) Determine the velocity (m/s) at the throat.
h) Determine the pressure (kPa) at the throat.
i) Determine the mass flow rate (kg/s) through the nozzle
j) Determine the Mach number at the exit.
k) Determine the temperature (K) at the exit.
l) Determine the velocity (m/s) at the exit.
