Finding the induced drag factor

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To find the induced drag factor for the aircraft, the key equation involves calculating drag using the parameters provided, including mass, wingspan, wing area, and drag coefficients. The user is struggling to eliminate the velocity and lift factors from the equation, which complicates the solution. It is suggested that since the aircraft is gliding almost level, lift is approximately equal to weight, which can help simplify calculations. Understanding the relationship between lift, weight, and drag is crucial for determining the induced drag factor. The discussion emphasizes the need for clarity in applying aerodynamic principles to solve the problem effectively.
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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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