1. The problem statement, all variables and given/known data As a project, I have had to design and build a scaled down version of a glider wing. The actual glider wing would be made of aluminium and have a length of 7.5m and have a uniformly distributed load of 30kg/m^2, the scaled down version is 0.9m and made of balsa wood. I want to work out the theoretical maximum deflection of my scaled down wing and then test it to compare results. For balsa wood E=16GPa, for aluminium E= 69GPa. second moment of inertia for the scaled wing is 5.72×10-10m^4 2. Relevant equations dmax=(UDLxL^4)/(8EI) 3. The attempt at a solution dmax=(UDLx0.9^4)/(8x16x5.72×10-10) dmax=(30x7.5^4)/(8x69xI) How do I scale down the UDL?