1. The problem statement, all variables and given/known data 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 2. Relevant equations the only equation i can think of is D=1/2pv2s(CD0+kCl2) 3. The attempt at a solution unable to figure a way out to eliminate the velocity factor and the lift factor. Please help! Thanks!