proppastie
Well-Known Member
The Carbon Dragon fabric covered aft portion of the wing has a drag brace from the end of the root rib to the spar diagonally, with a solid rib in between and another solid rib about 1/2 the span. My assumption which may or may not be correct is that this is for the 150# limit (225 ultimate) tip load when catching the tip of the wing (wing tip landing page 39 & 40 Basic Glider Criteria FAA)
When doing a truss analysis of this loading, of the main spar, drag brace, solid ribs, rear spar, tip and root rib, I can include the leading edge or not. Of course doing so gives much different axial loads for the drag brace and solid ribs and spars.
Is it reasonable to include the leading edge in the analysis, if so should I position the location of the member in the analysis at the most forward point?
When doing a truss analysis of this loading, of the main spar, drag brace, solid ribs, rear spar, tip and root rib, I can include the leading edge or not. Of course doing so gives much different axial loads for the drag brace and solid ribs and spars.
Is it reasonable to include the leading edge in the analysis, if so should I position the location of the member in the analysis at the most forward point?
Last edited:
