a$.$ An ideal rocket operates at a combustion chamber pressure of $3$

x$10^(6)$N$//$m$^(2)$ & expands to an ambient pressure of $3$xx$10^(4)$N$//$m$^(2).$

The specific heat ratio of the working substance is $1\mathrm{.}2$ and the gas

constant is $287$J$//$kgK$.$ If the temperature of the working

substance at the inlet of the nozzle is $2700$ K $,$ determine the

velocity at the throat, ideal exhaust velocity and nozzle expansion

ratio.

b$.$ The inlet conditions for rocket nozzle are given by total

temperature $2800$ K ; total pressure $43$ bar and the inlet velocity

can be neglected when compared to nozzle outlet velocity. The

nozzle throat diameter is $5\mathrm{.}2$ cm $.$ Estimate the mass flow rate

through the nozzle. Assuming optimum expansion at sea level,

determine nozzle exit velocity, exit Mach number and the thrust

developed by the rocket unit. Take ratio of specific heat as $1\mathrm{.}35.$