Hans,
If this is a flying wing put the CG at 15% chord.

IIF IT IS NOT A FLYING WING YOU HAVE WASTED YOUR TIME GIVING INCOMPLETE AND USELESS INFORMATION.

To work out a CG position you need to know the planform of the whole plane.
I have worked out that the MAC (Mean Aerodynamic Chord) is 484 mm, and that is as far as I can get.
We need to know if the wing is swept back. Is the LE at the tip further back that the LE at the root? And, by the way, the root is on the centreline of the aeroplane, not where it meets the fuselage. The semi-span or panle span or panel length is from the centreline to the tip.

We need to know if the model has a tail (or a foreplane) and how big it is and how far it is behind (or in front of) the wing. measure from the quarter chord point of the wing mean chord to the quarter chord point of the tail mean chord. That's the tail arm.

Tail Volume Ratio (TVR or Vbar) is
(tail net area divided by wing gross area) times (tail arm divided by wing MAC).

Vbar is usually between 0.5 and 0.7 for a pattern model.

CG position = 15 + 40 times Vbar as a % of MAC on conventional models

If Vbar is 0.6 that puts the CG at 39%, so your 41% is possible. Work it out.

And don't mention the high point of the section (max thickness?) in this context as it is irrelevant.

Alasdair