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Q. 3 (35 pt.) Air at 500K in a tank flows through a converging and diverging nozzle with throat area of 1 em and exit area of 2.7 cm2 When the mass flow is 0.05 kg/s, pitot tube reads py 250.6 kPa and 240 kPa at the exit plane. (a) (15 pt.) Is there a normal shock wave in the duct? Justify your answer. If so, compute the Mach number just downstream of the shock (b) (10 pt.) Compute the entropy change across the shock (c) (10 pt.) What it the velocity at the exit plane? Equation given: 207m 82-s1-8pIn TA-RIn , cp. 1.005 kJ/kgK, R-0.287 kJ/kg K
engineering   Mechanical-Engineering   
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