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From a polar curve of the entire aeroplane one can read:
  • A
    the minimum drag coefficient and the maximum lift.
  • B
    the minimum drag and the maximum lift.
  • C
    the maximum CL/CD ratio and maximum lift coefficient.
  • D
    the minimum CL/CD ratio and the minimum drag.

Refer to figure.
A polar curve describes the relation the lift coefficient and drag coefficient.

From the curve you can derive the:

  • Parasite drag coefficient; Find this where CL is 0
  • Minimum drag speed (VMD); this is the best glide Angle providing maximum range. Here the ratio of Lift over drag is the highest
  • VMP; Minimum power speed, here you find the minimum sink rate

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