… just to clarify…i think it has been said, but the NA is usually midway between the top and bottom assuming the shear stress distribution is symmetrical…to understand the NA you need to know that 1) it is simply a neutral plane where there is NO shear stress and 2) …
i appologise for nit-picking. but bert said something similar is the recent thread about balsa stringers. everyone is entitled to their own theories. but, when applied to engineering principles, some facts are just facts. I still believe the above statement is incorrect. i realise it’s been a long time for this stuff, but the couple betweeen the upper compressive layers and the lower tensile layers, still needs to be resolved (everywhere). I’m quite certain the “classical” defination of NA means that the local shear stress will be at a maximum, despite the fact that the principal tensile/compressive stress’ converge to zero. yes/no? -bill