**1. The problem statement, all variables and given/known data**

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**

Breguet Equation

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.

Cl=2L/ρV^{2}S

L=W (14000+2500)[itex]\times[/itex]9.81=161865N

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