Air is supplied to a covergent-divergent nozzle with a static temperature of 300 K, static pressure of 5 bar and a velocity of 150 m/s. The inlet area of the nozzle is 10 cm2. A normal shock occurs at a section of the nozzle where flow Mach number is 2. The flow Mach number downstream of shock corresponding to Mach number at the exit of the nozzle is 0.577. The flow Mach number at the exit of the nozzle is 0.4. Considering isentropic flow before and after shock and using isentropic flow relation for A/A* and Mach number provided below, find :
- throat area of the nozzle
- area of the nozzle where shock occurs
- exit area of the nozzle
- loss of stagnation pressure across shock.
Sketch the variation of pressure and Mach number along the length of the nozzle:
|
M
|
2
|
0.577
|
0.4
|
|
A/A*
|
1.688
|
1.22
|
1.59
|