As most of you know, commercial transport planes cruise at an altitude of approx

Question

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 ? air
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 C
D
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.)

http://tinypic.com/r/ir2goz/8

Density:

http://tinypic.com/r/2znpkyf/8

please show work

Explanation / Answer

The Minimum vertical separation in the US is 1,000 feet between airplanes... usually, airplanes will climb out over 2,000 feet per minute and most will continue the climb at or around 2,000 per minute... therefore, they would be approx 20,000 ft. above ground level 10 minutes after departure...

The "average" cruising altitude for medium-long haul flights, 1+ hours is in the 30,000's ...

Airplanes are not just flying around randomly, even though it may look that way from the ground... They would not route an airplane directly over Mt. Everest for the reasons you described as well as possible extreme turbulance from rising air coming off the mountain like a ramp...

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