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  • 14-04-2024
  • Engineering
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A commercial aircraft with a mass of 75825 kg, wing area of 112 m^2 and wing aspect ratio of 10 produces a maximum of 217427N of thrust. Assuming CLmax = 2.2 and CD0 = 0.04, Calculate the climb rate (in ft/min) at an initial climb airspeed of 131 knots.

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