I respectfully disagree. There are too many variables. Airfoil type i.e. Clark-Y, Modified Clark-Y, which generate increasing lift with speed. Semi-symmetrical or 2/3rds symmetrical. Then you have fully symmetrical. You can not use a 0-0-0 type incidence setting on a flat bottom Clark-Y airfoil BUT you can with a fully symmetrical at 0-0-0 BUT there are also variables with the fully symmetrical airfoil. The ideal setup for 0-0-0 is a model with the engine, fully symmetrical wing and stab, that are all centered longitudinally. Any deviation from this "neutral" engine and airframe setup results in engine thrust and wing/stab incidence variables.

The calculated CG in relation to the MAC remains constant. Everything else is a variable.

If all this technical stuff is cloudy and confusing to you ( original post ) then just stick with using the CG Calculator I offered in my previous post and that will get you in the air.

Stick to what is suggested on your plans or instructions concerning engine thrust and wing/stab incidences.