The point on the diagram corresponding to the minimum value of drag is:
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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