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Refer to figure.
The point on the diagram corresponding to the minimum value of drag is:
  • A
    point 4.
  • B
    point 1.
  • C
    point 3.
  • D
    point 2.

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, find this at the point of tangency
  • VMP; Minimum power speed, here you find the minimum sink rate
  • CLMAX; faster than this might damage the aircraft, it is the maximum value of CL in the chart

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