A toy rocket has a chamber pressure $($Pc$)$ of $1\mathrm{.}7$ atm and the ambient pressure $($Pa$)$ is $1$ atm.

The flow is optimally expanded and Pe $=$ Pa$.$ The chamber temperature $($Tc$)$ is $2700$ K$,$

molecular weight is $22,\backslash$gamma $=1\mathrm{.}2.$ The thrust produced by this rocket motor is $6$ N$.$ Calculate the

mass flow rate of gases through the nozzle, the specific impulse Isp, the thrust coefficient CF

and the throat area At of the nozzle. Sketch the nozzle that should be used