Dave, Forget what other information you got from somewhere else about the CG. Use that website to calculate where the CG should be for a stable flight. You will have to make some measurements and do a little drafting. First, measure the root chord, tip chord( ignore the wing tip), span (ignore the wing tip again) and leading edge sweep back ( ignore the wing tip again). Use those measurements to determine the following dimensions at that website;

A: With the leading and trailing edges projected to the center line of the fuselage you can now determine the A dimension
B: You have the B dimension from the wing tip chord.
S: Get S, the leading edge sweep, from the the drawing you just made.
Y: The half span Y is also available from the drawing.

Put in 30 in the "Enter %MAC Balance Point:".

Hit "Calculate CG:". This CG position is the correct one for your model. How does it compare to where you have it now?

I have a CAD program that I can do all this for you if you send me the dimensions of your wing and width of the fuselage.

Dan.