A general small-deflection theory governing the elastostatic extension and flexure of thin laminated anisotropic shells and plates is formulated. The plate or shell structure may be composed of an arbitrary number of bonded layers, each of which may possess different thickness, orientation, and/or orthotropic elastic properties. Donnell-type equations for cylindrical shells and Poisson-Kirchhoff plate equations are explicitly discussed, along with procedures for determining stresses in an individual lamina. Several methods of solution of the system of equations governing extension and flexure of plates are discussed and illustrated with examples. Optimization of laminate configuration is treated briefly. The results of a limited number of crack propagation tests of flat plate aluminum foil laminates in uniaxial tension are presented.