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Engineering, 25.11.2020 14:20 shadowsnake

The drag force FD on an airplane is a function of its velocity V , its length L, and the air density rho. The drag force is 0.3 N, when tested with a model plane at sea level, with a wind velocity of 10 m/s. What will be the drag force on a prototype that is 15 times larger and is traveling at 200 m/s at an altitude of 3 km?

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