What cruise velocity should the aircraft fly to maximize the cruise range?
Aircraft mass (excluding fuel), m0= 14000kg
Mass of fuel, mf = 2500kg
Specific fuel consumption of aircraft engine, sfc = 2.8[itex]\times[/itex]10-5 kg/N/s
Drag polar, CD = 0.02+0.08CL2
Planform area of aircraft wings, S = 65m2
2. Relevant equations
Coefficient of Lift
3. The attempt at a solution
I am trying to find the coefficient of lift but there has been no given velocity. I then try to find the velocity but there is no given coefficient of lift. I feel like I’m going around in circles.