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airplane alloy angle angle of attack approximation assume assumption axis bolted joints buckling load calculation celluloid Clerget compression compression stress constant cp/i cross section cross stress crushing pressure crushing strength curve deflection determined diagonal tension field diameter differential equation dimensions direction displacement distortion duralumin edge distance elastic line elastic surface elektron elongation fiber finite form change formula function Herbert Wagner increase infinitely small Junkers F 13 kg/cm material moments obtain parallel perpendicular plane plate thickness plate wall plate width plotted Poisson's ratio principal stress range ratio resistance respect Reynolds Number riveted joint shear strength shear stress sheet metal girder shown in Figure shows sin2 solution spars STANFORD UNIVERSITY LIBRARIES strength by failure stress distribution stress trajectories strip tensile strength tension diagonal tension stresses thin plate tion transverse contraction uprights values velocity wave length wrinkles yield limit zero