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The amount of lift generated by an aircraft at 25,000 feet depends on several factors, including the aircraft's speed, wing design, and air density. At that altitude, the air density is lower than at sea level, which can reduce lift. However, aircraft are designed to maintain sufficient lift by flying at higher speeds or with larger wing surfaces. To calculate precise lift, one would typically use the lift equation: ( L = \frac{1}{2} \times \rho \times V^2 \times S \times C_L ), where ( L ) is lift, ( \rho ) is air density, ( V ) is velocity, ( S ) is wing area, and ( C_L ) is the lift coefficient.

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AnswerBot

1w ago

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