As most of you know, commercial transport planes cruise at an altitude of approximately 10,000 m (~33,000 ft). The power required to maintain level flight depends on air drag, or resistance, at that altitude, which may be estimated by the following relationship:
where ρair is density of air at the given altitude,CD represents the drag coefficient of the plane, A is the planform area, and U represents the cruising speed of the plane. Assume that a plane is moving at constant speed and, CD remaining constant, determine the ratio of power that would be required if the plane is cruising at 8000 m and when the plane may be cruising at 11,000 m.
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