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Finding the induced drag factor

  1. May 6, 2017 #1
    1. The problem statement, all variables and given/known data
    An aircraft has a mass of 1100kg and a wingspan of b=9.75m. the surface of the wing is 15m2 and its span effciency factor e=0.90. the parasitic drag at zero lift of the aircraft CD0 is 0.0225. Take density of the air to be 1.225kg/m3

    The aircraft has lost power and is gliding to the ground. Assume that the glide angle ϒ is small

    2. Relevant equations
    the only equation i can think of is
    D=1/2pv2s(CD0+kCl2)

    3. The attempt at a solution
    unable to figure a way out to eliminate the velocity factor and the lift factor.

    Please help! Thanks!
     
  2. jcsd
  3. May 6, 2017 #2

    FactChecker

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    What can you estimate/conclude from the fact that it's almost level flight?
     
  4. May 7, 2017 #3
    that Lift would be equal to Weight?
     
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