Where P is the desity of the air at the given altitude C represents the drag coe

Question

Where P is the desity of the air at the given altitude C represents the drag coefficent of the plane, A is the platform area, and U represents the cruising speed of the plane. Assume that a plane is moving ata constant speed and C remaining constant, determine the ratio of power that would be required if the plane is cruising at 8,000 meters to the situation when the plane maybe cruising at 11,000 meters (desity of air values listed below) please refer to image for equation.

8,000 meters 35.66 Atmospheric Pressure (kPa) Air density 0.526 (kg/m^3)

11,000 meters 22.70 Atmospheric Pressure (kPa) Air desity 0.365 (kg/m^3)

2. 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 Power EP.c,AU ' Where P is density of air at the given altitude, C , represents the drag coefficient of the plane, A is the planform area, and US represents the cruising speed of the plane. Assume that a plane is moving at constant speed and C remaining constantdetermine 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.) 3 lise the rannical method discussed in this chapter to obtain the solution to enhancemhical method

Explanation / Answer

Only density of air will vary.

Hence ratio of power at 8000 m and at 11000 m =rho1/rho2 = 0.526/0.365 = 1.441

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