A rocket operates at sea level with a chamber pressure of $20$ atm, a chamber temperature of $2000$

K$,$ and a mass flow ofm$=1$ kg$/$s$.$ Gas properties are taken as constant and are known to be

Cp$/$Cv$=1\mathrm{.}3,$ Cp$=0\mathrm{.}36$ kcal$/$kg K and R$=350$ J$/$kg K$.$

$1.$ Show graphically the variation of the area, A$,$ density, $,$ velocity, V$,$ and Mach Number,

M$,$ with respect to pressure in the system. Can the throat location be identified from these

plots?

$2.$ Comment on plotting the results vs$.$ pressure instead of position. What is the utility in

plotting vs$.$ pressure?

$3.$ Calculate the ideal thrust and the ideal specific impulse.