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How to find the induced drag factor

  1. May 8, 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
    Find the induced drag factor k.

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

    3. The attempt at a solution
    Assuming almost level flight L=W=1100kg
    unable to figure a way out to eliminate the velocity factor

    Please help! Thanks!
     
  2. jcsd
  3. May 13, 2017 #2
    Thanks for the thread! This is an automated courtesy bump. Sorry you aren't generating responses at the moment. Do you have any further information, come to any new conclusions or is it possible to reword the post? The more details the better.
     
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