Scale Soaring UK

Hello everyone
Im currently restoring a 70s vintage Avoncraft Slingsby T53 Phoenix 2 channel glider that has been languishing in the loft for nearly 20 years!
Anyway all progressing well but would anybody out there know/remember where the suggested C of G should be please?

I hopefully have attached a couple of stock pictures of the model to jog any memories into action.
Cheers
Paul Callaghan

With its straight non tapered wing and generous tail area I would start with a CG of 28 to 30% of the wing chord back from the leading edge.

AEB

Thanks John
The pictures don't show it but there is a massive amount of forward sweep to the wings ( a bit like the original).
I will probably work slowly backwards from the leading edge if I cannot find any definitive information from previous owners.
thanks for the help though.
Paul.

Try this:-

https://rcplanes.online/cg_calc.htm

Start with the static margin at 15% for safety

BC

I'd put my money at somewhere near the LE

Thanks everyone for you help.
Chris is the second person to say the 'leading edge' so I will start there and gradually work backwards.
I will put a picture up when I have finished it for interest sake, attached is a picture of the model once I had finally got the god awful solarfilm off the wings.
The canopy is in 'poor' shape, and I have made a new stab.
The fus has gone a lovely shade of 'old english white' but I am reluctant to repaint it - to be fair it does go with the vintage look but now the wings are covered in pristine white Oracover it does look somewhat odd!
Anyway to be truly scale it should all be light grey....
So again thanks for the help chaps and I will stick a couple of photos up when its done.
Many thanks
Paul

hi I built a 4.2 meter one and I balanced it on the l.e at the root at fuz end.

john greenfield wrote: ↑30 Apr 2020, 08:45 With its straight non tapered wing and generous tail area I would start with a CG of 28 to 30% of the wing chord back from the leading edge.

AEB

Paul
You may have misunderstood my comment. The CG should always be referenced to the mean aerodynamic chord, not some arbitrary location at the wing root. With a straight non tapering wing the mean aerodynamic chord will be at the 1/2 span of the wing panel. Locate this point and go back 28 to 30%.

AEB

Hey thanks for that John.
Hope all well with you.
Best
Paul