The problem exists only with the GU canard and
wing tip gear. Extending the spar caps to the tip
will change the resistance to stress, but will
possibly change the flight characteristics and
definitely the taxiing roughness. It will also
increase the weight of the plane. The original
designer used "best design practices", but
ignored the fact that those practices did not include gear at the wing tips.
At 07:29 AM 12/24/2012, you wrote:
Are you building a TriQ and are you building to the Waddlow Canard design?
On Dec 24, 2012, at 3:00 AM, "johnogr300"
Hi allweakest part of the canard wing is at the end
I have read where it was said that the
of the stiffener, cracks have been found at this point.
To all you aeronautical engineers couldanybody tell me if it would be a good idea to
run the stiffener to the end, or tip, of the canard.
I`m building the LS1 profile canard without the carbon spare.[Non-text portions of this message have been removed]
I`m fitting a Viking engine.
18242 Peters Ct
Fountain Valley, CA 92708
[Non-text portions of this message have been removed]