At a given altitude, the drag power for a certain propeller-powered airplane of ...
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At a given altitude, the drag power for a certain propeller-powered airplane of mass m = 1000 kg is given by Pr = 0.10 v3 + 0.04 W2/v (where v is given in ms−1), and the available engine power can be considered independent of speed and approximately Pa = 120 kW. What is the maximum rate of climb (R/C) this airplane can achieve at this altitude? (take g ≅ 10 ms−2)
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