The growing trend of fibre reinforced composite laminates in highly loaded structural applications has created a need for better analytical tools to provide quick estimates of predicted laminate performance, faster computational tools for more detailed laminate analysis, and more experimental data for validation of higher order theories. The production of experimental data requires significant capital investment. As such, the majority of research being conducted is focused on developing higher order theories and reducing computational effort to be able to more accurately simulate composite laminates in various load cases. However, due to the lack of available experimental data, the theoretical research being conducted is most often validated against the 3D elasticity theory, which itself is very computationally intensive, albeit highly accurate. One example of a highly loaded composite structure with a thick cross-section is a helicopter’s main rotor yoke. Industry experience has determined that the thick section of such a laminate is the most critical, especially around the area of load introduction due to a bolted joint connection. This study aims to provide reliable experimental data against which a higher-order monodimensional beam theory is compared, and that can be used to validate other higher order theories. Rectangular laminates of 20, 40, 60, and 80 unidirectional layers along with 80 cross-ply layers are tested in quasi-static cantilever bending at 5 mm/min, where the fixed end of the laminate is clamped between steel plates and the loaded end is clamped between the cylindrical faces a cantilever loading fixture. Laminates of 80 unidirectional layers are also tested in cantilever bending where the loaded end is also clamped between steel plates to represent a bolted connection at both ends of the specimen.  Digital image correlation and strain gauges were used to collect surface strain measurements which were used to validate a fully parametric ANSYS model that could predict failure based on Hashin failure criteria. The train data showed that digital image correlation is a valid technique for full-field surface strain measurement up to very high displacement and strain levels. The load-displacement data was compared to higher-order monodimensional beam theory calculations and showed the limitations of this theory as specimen thickness increased, as well as the accuracy it can provide for thinner laminates, even when including secondary bonded components such as buffer pads. A simplified method for using the monodimensional beam theory is presented for the quick calculation of the shear correction coefficient of a [0/90]Ωs laminate, where Ω can be any integer. The failure displacements of each specimen configuration are charted against laminate thickness to illustrate the size effect, which is the principle of decreasing component strength with increasing thickness, as it relates to composite plates in bending.