The take$-$off gross weight is $27,000lb$ which includes $1600$ lb of reserve fuel and $8,400lb$ of climb$/$cruise fuel.

Create functions that calculate the atmospheric properties, the drag and the thrust and SFC$.$ To calculate the drag you need CDO$(M)$ and $K(M).$

Calculate the flight envelope $($detayli bir sekilde a$$iklayarak $$iziniz$!)$

Calculate the maximum distance trajectory in cruise.

Calculate the minimum time trajectory in climb