For a small turbojet $($JCA $71113-0000)$ with Jetcat RX engine specifications:

Consider the general Thrust equation for a Turbojet:

$F=\frac{m_9^{}{V}_9-m_0^{}{V}_0}{g_c}+(P_9-P_0)A_9$

Assume if you are designing a variable thrust augmentation system for the turbojet as illusterated below:

nozzle$)$

Define the area ratio as:

AR$=$A$\_$e $($variable nozzle$))/$A$\_$e $($default nozzle$)$

Use the continuity equation to calculate the exhaust equation, and incoporate the modified thrust equation.

Deliverables on a single slide:

Show your reformulated thrust equation

$**$List paramters used $($constants$)$

$**$Plot Thrust vs AR: