NOZZLES AND JET PROPULSION

QUESTION $1$

$[20$ MARKS$]$

The gases move through the propulsion nozzle as seen in Fig. $1$ and increase in volume from an initial pressure of $5$ bar and a temperature of $430C$ to a lower pressure of $1$ bar. The gas flows out of the nozzle at a rate of $20k\frac{g}{s}.$ Assuming: that the discharge coefficient is $0\mathrm{.}97$ and the nozzle coefficient is $0\mathrm{.}90.$ The properties of the gases can be described by the specific heat ratio $,$ equal to $1\mathrm{.}222,$ and the specific heat capacity $c_p,$ equal to $1\mathrm{.}11k\frac{J}{k}g.k.$ Additionally, it is assumed that the initial velocity of the gases is negligible.

$1\mathrm{.}1$ Draw the T$-$S diagram.

$1\mathrm{.}2$ Calculate the required throat and exit areas of the nozzle.

Fig$\mathrm{.}1.$ Convergent$-$Divergent Nozzle.