An engine is flying at $M=0\mathrm{.}85$ at an altitude of $27000ft.$ The maximum temperature that the turbine can handle is $2800$ K $.$ The compressor pressure ratio, $PR=35.$ Make assumptions for any other variables you need. Using the equations derived in Lecture $17-18,$ compute the thrust of the engine for efficiency values of $1,0\mathrm{.}9$ and $0\mathrm{.}8($i$.$e$.,$ set all the $$ values and rc to the same for each calculation$)$ What is the loss in thrust because of the inefficiencies? Report the answer in the form of this table.

$\backslash$table$[[{}_n={}_t={}_c={}_b={}_d=rc,$Specific Thrust $(k-N\frac{s}{k}g)$