Has anyone done any stress analysis on the outer main spar built to the
dimension on the early plans that showed the outer end at 5 ½ instead of 5 ¼ .
When trimmed down to the wing tip airfoil thickness the spar cap height is 7/16?
on top and bottom. I have found this to be the case with my sp
I was thinking of using the AS5046 airfoil which takes more of the spar caps
than the RAF48 by virtue of the more extreme angles. The original plans only
differ in dimension at the wing tip end, so that when shaved to size the largest
discrepancy is at the outer most end having the least load.
My experience tells me to use a well proven product developed for the
application. While T88 may be a fine product and I'm sure that its cured
strength is much greater than the spruce that it is bonding, there are other
products. I started aircraft building in the late 70s. T88 was new and onl
Thanks for the responses... its good to hear of Danny Livingstone's EPS
aircraft. Many of the responses related to cost or the sanding ability of this
material. You are correct, EPS is very difficult to sand to shape due to it's
make-up. I wouldn't think of trying to sand it to shape, howev
I am contemplating the use of white EPS for tail feather construction.
A KRnet search revealed no entries related to expanded polystyrene foam for use
in KR construction. I found several entries on extruded polystyrene foam colored
blue, pink or green in 2lb density. Has anyone used the 1lb wh
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