sheet3.pdf - Assignment#3 Shock Waves(1 A supersonic nozzle...

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Assignment #3 - Shock Waves (1) A supersonic nozzle has throat and exit diameter of 1 and 1.4 cm respectively, the nozzle is supplied with air at 810 kPa and 150 C, find a. The change in back pressure in order to move the shock wave from the throat to exit section . b. The back pressure which locates a shock at an area 20% greater than throat area .
1 (2) A convergent divergent nozzle is designed for Mach number of 3. The nozzle is supplied with air at 1.013 MPa and discharges into a space where the pressure is 557.2 kPa. Check if there is a shock or not. Find its location . (3) The exit area of a convergent-divergent nozzle is three times the area of the throat. The stagnation pressure of air at entry is 2.5 times the static pressure at exit. Neglecting all losses except that due to shock in the divergent portion of the nozzle, determine the Mach number and the area at the section were the shock occurs, the exit Mach number and the increase in entropy across the shock .

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