Based on input from a fellow builder in Australia I have done some redesign work on my planned wing espically with regard to material. The first big change was to use Carbon Fiber Rods for the spar caps rather than the UNI S2 tape in the Vision plans. The second change was to go to a two piece wing with overlaps inside the fuselage for attachment. A third refinement was to make a large section of the outboard wing removable at a point where the wing can be reconfigured from LSA compliant to being ""Normal"". For now I am constrained to LSA but I have my hopes and I want this wing to be convertable.
1) Some samples of CF Rod purchased from Wicks. These are 0.060 and 0.080 inch diamter materials and they have been cut to 2' lengths for an experimental wing spar project I am starting. That experiemnt will have a piece of Last-A-Foam 3/8" x 2" x 24" for a core forming the basis for the shear web. The CF Rods will be bonded to the thin edges to form a spar cap. Additionally there will be Phenolic hard points so one end can be rigidly attached and the test spar loaded to see how well the materials and techniques work out. Materials are also available through Aircraft Spruce and John Marske who sells a handy manual on aviation applications for the materials.
2) This is the revised wing planform featuring the removable outboard panels. The spar is continued into the large wingtips to provide extra strength for their attachment. Solid core is used in the outboard area for light weight and easy build. The wing itself is now tapered and has a 15% thick airfoil at the root and tip. Not using a thinner airfoil sectiont(i.e. 12%) at the tip does not fo;;ow commom practice bu it is done to eliminate tip stall without the need for washout following the advice of Mr Harry Riblett.
3) More detail of the wing spar showing hardpoints and taper, both in height and thickness. The outboard wing panels have a phenolic tab that will fit into a pocket at the end of the inboard panels and be secured with four bolts through the ph
