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A small aircraft has a wing area of 35 m^2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.035. The density of standard air at sea level is 1.225 kg/m^3.* Awing 35 m² 4000 kg C₂-0.45

A small aircraft has a wing area of 35 m^2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.035. The density of standard air at sea level is 1.225 kg/m^3.* Awing 35 m² 4000 kg C₂-0.45

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A small aircraft has a wing area of 35 m^2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.035. The density of standard air at sea level is 1.225 kg/m^3. Awing 35 m² 4000 kg C₂-0.45
Transcribed Image Text:A small aircraft has a wing area of 35 m^2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.035. The density of standard air at sea level is 1.225 kg/m^3. Awing 35 m² 4000 kg C₂-0.45
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