If I have two spars running through an airfoil, which can be assumed to be two dimensional, which method would I use to find the stresses at the points where the spars are fixed? The loads would be lift and drag and what I need are the bending and shear stresses. Because I have more than one spar, I am looking at a statically indeterminate problem.
Another question, my professor said that to simplify the problem, I can apply the lift and drag forces at the quarter chord point. Would these forces act on the mean camber line or at the upper or lower surfaces?
The Attempt at a Solution
I don't think I've been taught how to do this yet. I am willing to read ahead but I don't know what I should be reading. I have access to the Beer and Johnston Mechanics of Materials textbook
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