What is the best way to mathematically calculate values of lift and drag forces, in different phases of flight: takeoff, climb, cruise, descent, and approach?
Edit: I have the idea of calculating the lift force by using the information of speed and angle of attack (for the coefficient of lift value) in different flight phases from the pilot's "flight manual" (if it is obtainable there), in standard ISA conditions L=CL*(r+v⌃2/2)x wing area. For drag, I would use same inf. and the total drag coefficient is equal to the drag coefficient at zero lift, plus the induced drag coefficient Cd = Cd0 + Cl^2 / ( pi * Ar * e), where The efficiency factor (e) is equal to 1.0 for an elliptic distribution and is some value less than 1.0 for any other lift distribution. –