I am interested in designing a scale model semi-monocoque wing for a glider. I've done some research on the framework and internal structure. I have found out about the spars, ribs and stringers and I am trying to produce a design with the highest strength to weight ratio. I am planning on making the wing 0.5m long with a chord length of 0.1m along the cross section (so no tapering).
If anything is unclear please let me know. In my first diagram, I have placed 2 spars through the wing about 10% of the chord length from the leading edge and 15% from the trailing edge, leaving 75% of the chord length between the two spars.
In the second diagram is a rough plan of how many ribs would be used and where they would be placed: the solid outline is the wing outline, the thick black lines are the spars and the dashed lines are the ribs.
I have used a triangular configuration, as the triangle is the strongest shape and resists shear, torsion, compression and tension better than any other shape. Then I have placed a rib going down from the top corner of each of the 3 triangles to the bottom of each. Then I have placed ribs (or stringers) between each of the bottom corners of the triangles.
My question is, how can I improve or optimise that design? Is there a certain number of triangles I should use and how big should they be relative to the wing? Should they be equilateral triangles or is isosceles stronger? Also, how many ribs should I be considering using?
I'm not looking for anyone to figure out exact quantities. If there is some kind of calculation I need to carry out to find the optimal number or triangles and ribs, I would be happy to do that. Unless it is way beyond A-level maths/physics standard then I probably will not be able to do it. But I would like advice on how I can figure it out. If my question is vague or unclear, please inform me, and I will gladly edit it.