Finding the induced drag factor

[Tomdickjerry]

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 C_D0 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(C_D0+kC_l²)

The Attempt at a Solution

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

Please help! Thanks!

 

[FactChecker]

What can you estimate/conclude from the fact that it's almost level flight?

 

[Tomdickjerry]

that Lift would be equal to Weight?