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Aircraft Performance Question -- Berguet

  1. Jun 30, 2014 #1
    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+0.08CL^2
    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
     
    Last edited: Jun 30, 2014
  2. jcsd
  3. Jul 1, 2014 #2

    Simon Bridge

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    Are you not assuming uniform level flight?
    Does that not make the lift equation rather simple?

    How about showing the details of the working, with reasoning, that you have already.
     
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