'lemme give you some facts and figures here.
The overall length of the fuselage is 45 1/4" long.
The C.G. (Per the plan) sits at 30% and 70% of that.

Wing chord is 11.9 inches, and the C.G. sits at 4.25 back from leading edge or at about 35% of the chord. This is not at Max. thickness, for that is at about 37% back.

Problem being is that due to lighter weight equipment now, the C.G. measures out to about 9/16" aft of the plan noted C.G. To which I think if I move the wing towards the aft about 1/2 inch, plus add a bit of ballast forward of the C.G. I then would be able to bring the nose tire in contact with the asphalt.

As the whole aircraft is lighter now, the general performance ought to improve aerobatically.

Wm.