Battson
Well-Known Member
Is there a simple formula which one can use to analyse the stress within a simple wing, of constant chord, shape, and with zero twist or washout?
Perhaps there is a simplified form of the Schrenk approximation which removes the form factors and rate of twist variables?
I really just want to know how the stress born by the wing varies with distance along the wing. Specifically I am interested in strut-braced wings. I would prefer to refer to an accepted text online, if at all possible.
I have had a hard time finding a credible source of knowledge in this area, short of purchasing texts. I am betting I haven't looked in the right places.
Perhaps there is a simplified form of the Schrenk approximation which removes the form factors and rate of twist variables?
I really just want to know how the stress born by the wing varies with distance along the wing. Specifically I am interested in strut-braced wings. I would prefer to refer to an accepted text online, if at all possible.
I have had a hard time finding a credible source of knowledge in this area, short of purchasing texts. I am betting I haven't looked in the right places.