As most of you know, commercial transport planes cruise at an altitude of approximately 10,000 m...

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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: PowerPC AU Where p is density of air at the given altitude, C_ represents the drag ePi D 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 C remaining constant, determine the ratio of power that would be required if the plane is cruising at 8,000 m to the situation when the plane may be cruising at 11,000 m. (Please refer to Table 10.3 on page 249 of your textbook for the values of density of air.) 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: PowerPC AU Where p is density of air at the given altitude, C_ represents the drag ePi D 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 C remaining constant, determine the ratio of power that would be required if the plane is cruising at 8,000 m to the situation when the plane may be cruising at 11,000 m. (Please refer to Table 10.3 on page 249 of your textbook for the values of density of air.)