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Q3. An aircraft having a take-off mass of 36500 kg and a wing area of 95 m² fitted with turboprop engines of total power 10000 kW, assumed not to vary with speed, and propellers of 87 per cent efficiency. The drag polar for the aircraft is: C₂-0.0145+0.052C₂² At sea level: (a) Calculate the coefficient of lift at minimum required power, associated speed and the minimum power required for steady level flight. (b) Calculate the maximum rate of climb and angle of climb available to the pilot.
Transcribed Image Text:Q3. An aircraft having a take-off mass of 36500 kg and a wing area of 95 m² fitted with turboprop engines of total power 10000 kW, assumed not to vary with speed, and propellers of 87 per cent efficiency. The drag polar for the aircraft is: C₂-0.0145+0.052C₂² At sea level: (a) Calculate the coefficient of lift at minimum required power, associated speed and the minimum power required for steady level flight. (b) Calculate the maximum rate of climb and angle of climb available to the pilot.
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