Air enters a constant-area duct at Mach 3 and stagnation conditions 1,000 K and 1.5 MPa. In the duct it undergoes a frictionless energy-transfer process such that the exit Mach number is unity. Consider two cases: a) a normal shock at the inlet to the duct b) shock-free supersonic heating Determine the stagnation temperature and pressure at the exit in each case above. Is there any reason why the total energy transfer should differ (or be equal) in the two cases?

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A: To = 527 +273 = 800K Po = 1 MPa  Mass flow rate = 2.86 kg/s

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Q: e end of the pipe. If the number, the mass flow

A:

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A: Given data P0=170 KPaT0=300 KM=0.2

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A:

Q: Air flows through a constant area combustion chamber that has a diameter of 0.15 m and a length 5 m.…

A: D=.15 mL= 5m P0=1.4 Mpa T0=335 KM1=.55

Q: verging-diverging nozzle of ave occurs at the exit plane

A: Determine the value of pressure and temperature before the shock.

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A: Since you have posted a question with multiple sub-parts, we will provide the solution only to the…

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A: Given Data