Aircraft Performance Question. Berguet

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/ρV2S
L=W (14000+2500)[itex]\times[/itex]9.81=161865N

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