A converging-diverging nozzle with an exit to throat area ratio of 4.0 is designed to expand air isentropically to atmospheric pressure. Determine the exit Mach number at design conditions and the required inlet stagnation pressure. Also, calculate the back pressures corresponding to the various flow regimes for the nozzle.

Answer

0.9, 1172.35kPa

Explanation:

Question (in proper order)  Attached below

Air is flowing inside the throat has following inlet conditions

'u' is the speed of sound in the air

Therefore volumetric flow rate entering,

Using ideal gas equation

PV=nRT

=0.117878 gmoles/sec

Therefore , mass flow rate

Given

Using continuity equation

Hence exit velocity = 306.261 m/sec

Exit Mach number

Temperature will remain same as 500 K

Now

Using Bernoulli's equation

Here

answer:

explanation:

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