1. The problem statement, all variables and given/known data Flying aircraft X is designed in 2014. The current model has a top speed of 812 m/s, a mass of 72,000 kg when fully loaded, and a maximum thrust to weight ratio of 0.44. Calculate the lifting force and the drag coefficient for the Quinjet when it is flying level at top speed. Assume turbulent flow. 2. Relevant equations Drag Coefficient: Fd = cd 1/2 ρ v2 A 3. The attempt at a solution I do not understand how lifting force work(teacher didn't bother to teach us before assigning the homework) and can only calculate drag coefficient given the surface area.