In this article, we cover pressures and temperatures of a DeLaval nozzle. A DeLaval Nozzle is a nozzle that contains a convergent and divergent section (see image below) that resembles a hourglass figure. The nozzle is capable of accelerating gases to supersonic speeds which makes it an attractive proposition for rocket engine nozzles!
Note: To help solve this problem I used An Engineering Data Book
Below is a problem you may encounter during university, calculating pressures and temperatures seen in the nozzle.
a) Air at specific heat ratio k= 1.4 and specific gas constant R = 287 J/(kgK) travels through a Mach 2.8 convergent-divergent DeLaval nozzle. The inlet stagnation temperature To1= 290 K and the inlet stagnation pressure po1 = 3700 kPa.
Assuming the flow is isentropic, determine p*, T*, and the critical density. Calculate the nozzle exit temperature
T3 and the exit pressure p3
at the fully expanded nozzle condition.
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