Finding the induced drag factor

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SUMMARY

The discussion focuses on calculating the induced drag factor for an aircraft with a mass of 1100 kg, wingspan of 9.75 m, and a wing surface area of 15 m². The span efficiency factor is given as e=0.90, and the parasitic drag at zero lift (CD0) is 0.0225. The equation for drag, D=1/2pv²s(CD0+kCl²), is presented, but the user struggles to eliminate the velocity and lift factors to find the induced drag during a glide scenario. The conclusion drawn is that during level flight, lift equals weight, which is critical for understanding the aircraft's performance in a glide.

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Tomdickjerry
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Homework Statement


An aircraft has a mass of 1100kg and a wingspan of b=9.75m. the surface of the wing is 15m2 and its span effciency factor e=0.90. the parasitic drag at zero lift of the aircraft CD0 is 0.0225. Take density of the air to be 1.225kg/m3

The aircraft has lost power and is gliding to the ground. Assume that the glide angle ϒ is small

Homework Equations


the only equation i can think of is
D=1/2pv2s(CD0+kCl2)

The Attempt at a Solution


unable to figure a way out to eliminate the velocity factor and the lift factor.

Please help! Thanks!
 
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What can you estimate/conclude from the fact that it's almost level flight?
 
that Lift would be equal to Weight?
 

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