Thorp Air Command - T18.net

Good points to be aware of. I don't know. It would have to be specifically engineered. I can tell you the spin resistance would be less, not sure about the structure.
Cubes

comment -- [One thing that crossed my mind was the addition of at least 30 lbs or more weight placed at the extreme end of the spar. What does that additional weight, maybe more importantly, the additional moment may due to the fatigue and/or G loading of the wing? Maybe it is of no concern, but the original design by an aerodynamic and structural engineer John Thorp or Lu Sunderland I do not believe included that weight and moment acting through the spar and the connection.]

Tip tanks on a Thorp are just a bad idea - don't do it!

comment -- [On the other hand, wet wings were not contemplated either and yet that is accepted. I do not know what engineering calcs if any were done for wet wings. However the weight of the fuel is distributed over the entire D-section, rather than concentrated at the tip.]

They were not originally considered as the standard Thorp does not need any additional fuel .. that being said when Don Taylor needed to fly around the world wet wings were considered and analysed .. the biggest impact is on gross weight. Those figures are available (g-loading and respective gross weights)

_________________
Lee Walton
Houston, TX
N51863,N118LW
KEFD

Taxiing is the issue. Wings support themselves in flight.

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Bob Highley
N711SH
SN 835
KLAL