Air flows through a converging-diverging nozzle/diffuser.Assuming isentropic flow, air as an ideal gas, and constantspecific heats determine the state at several locations in thesystem.
Note: The specific heat ratio and gas constant for air are given ask=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 theinlet.

c) Determine the stagnation pressure (kPa) at theinlet.

d) Determine the theoretical throat area (cm^2) for sonic flow(A*).

e) Determine the Mach number atthe 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 thenozzle

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.