An airplane weighs 180 kN and has wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise.

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An airplane weighs 180 kN and has wing area of 160 m².
(a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient.
(b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise.
Transcribed Image Text:An airplane weighs 180 kN and has wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise.
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