Your aircraft (Weight = 2000 N) is about to take off with a lift coefficient of CL = 0.9. Perform the following calculations and show all your work: 1- Take off Speed (Hint: Assume that your wing Area is 10 m^2 and that the take off is happening at sea level where density is rho = 1.225 Kg/m^3 - Ignore the effect of the stabilizer on lift).

2- Lift coefficient at altitude assuming a cruising speed V= 225 m/s (Hint: Apply the same formula as before)

Which condition will be closer to the stall velocity? Explain why.