Quote:
Originally Posted by BBerson  Also, the first wing needs to be load tested. More often than not, the spar will start to buckle before the calculated ultimate load is reached. Better to find the weak point before flight. |
Couple of questions for those in the know.
1) What would it typically cost to get a comprehensive stress/flutter analysis done on a small conventional single seat design?
2)I hope this isn't a dumb question but as far as actual load tests go. Would a properly scaled down version of the full size wing and other components be suitable. IOW say a 1/2 scale, in all respects, wing built with the same materials and construction technique's as the projected full scale. Would an ultimate load test of the scale wing be valid/usable?