I am fairly new to aerodynamics and I am trying to create a flight simulation based on data available for F-4E Phantom.
I found various flight test data for this particular aircraft and trying to create lift coefficient slope vs AoA.
So, as far as I know, I can calculate the lift force from this for the whole aircraft. This will be sum of wing, elevator, fuselage and engine lift. Can I use wing area as reference to calculate lift coefficient? Can I use this coefficient to find tail lift force? There isn't any AoA indicator in these data, so I can't really draw the slope from this. Any direction to what can I do or what SHOULD I do will be much appreciated.