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Air at an absolute pressure 60.0 kPa and 27 enters a passage at 486 m/s. The cross sectional area at the entrance is 0.02 m2.

At section 2, further downstream, the pressure is 78.8 kPa(abs). Assuming isotropic flow. Calculate the mach no. at section 2. Also identify the type of nozzle.

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Data:-

P1=60kPa=60×103Pa,P2=78.8×103Pa

T1=27=300K,V1=486m/s,A1=0.02m2

To find:-

(i)M2=?

(ii)Type of nozzle=?

Solution:-

At section (1) since velocity

C1=γ.R.T1=1.4×287×300=347.188m/sec

Mach no. at section (1)

M1=v1c1=486347.188=1.3998

Now, stagnation pressure at (1)

P01=P1[1+γ12M21]γγ1=60×103[1+1.4+12×(1.3998)2]1.41.41

=190.887×103Pa

For sentropic flow …

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