A convergent-divergent nozzle has an exit area ratio of 2. Air enters the nozzle with a stagnation pressure of 950 kPa and a stagnation temperature of 350 K. The throat are is 490 mm2. Determine the mass flow rate, exit pressure, exit temperature, exit Mach number and exit velocity for the following conditions :
(i) Sonic velocity at the throat, diverging section acting as a nozzle.
(ii) Sonic velocity at the throat, diverging section acting as a diffuser.
Table below gives the one-D, isentropic, compressible flow functions for an ideal gas. * represents the critical values at the throat where the Mach number is unity :
|
M
|
M*
|
A/A*
|
p/p0
|
T/T0
|
|
0.308
|
0.326
|
2.00
|
0.936
|
0.9812
|
|
1.00
|
1.00
|
1.00
|
0.528
|
0.8333
|
|
2.197
|
1.717
|
2.00
|
0.0939
|
0.5089
|