Problem 2 - [3 points] Consider air flowing through an adjustable C-D nozzle. The atmospheric pressure is p_(a)=0.1 bar. The throat area A_(t)=0.125m^(2) and the exit area is A_(e)=0.5m^(2). The reservoir temperature is 1000 K. (a) Determine the reservoir pressure, nozzle exit pressure, and nozzle exit Mach number when a shock occurs within the div

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Problem 2 - [3 points] Consider air flowing through an adjustable C-D nozzle. The atmospheric pressure is

p_(a)=0.1

bar. The throat area

A_(t)=0.125m^(2)

and the exit area is

A_(e)=0.5m^(2)

. The reservoir temperature is 1000 K. (a) Determine the reservoir pressure, nozzle exit pressure, and nozzle exit Mach number when a shock occurs within the diverging section of the nozzle at

(A)/(A_(t))=2.0

. (b) Determine the mass flow rate and thrust. (c) Reclassify the nozzle flow if the nozzle exit area is reduced to

0.250m^(2)

. Use the same reservoir pressure computed from part (a). Also, determine nozzle exit pressure and Mach number. HINT: Verify that exit mach number is 0.468 (d) Determine the mass flow rate and thrust for the scenario described in part (c).

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