Problem Description

For the specific aircraft, the lift coefficient for a 6^o angle of attack is determined by

     C_L = 0.3(1 + 0.2(6)) = 0.66

In order for takeoff, the lift should be balanced by the weight of the aircraft. That is, L = W = 3,500 lb_f.

From the definition of lift,

     L = C_L ρAV²/2

where ρ is the density of the air. Using the tables, ρ is found to be 0.00238 slugs/ft³. A is the planform area, which is 350 ft².

The takeoff speed can then be calculated as follows: