We investigate the structural performance of composite wings employing shallow biangle and thin-ply laminates via experiments. Shallow bi-angle fabrics oriented in the direction of wing span increase the longitudinal stiffness of a wing at a cost of relatively low decrease in transverse stiffness. The thin-ply increases the laminates resistance to micro-cracking and delamination. These features can increase bending stiffness and failure load of a wing. To verify this, we design, fabricate, and test composite wing structures with shallow bi-angle and thin-ply laminates. Specifically, by conducting static bending tests aided by laser Doppler vibrometry, we show the superior structural performances of these wing structures in comparison with a reference wing manufactured using conventional ply. This shallow bi-angle and thin-ply technique can open new routes to designing composite structures with improved stiffness and strength properties along with cost-effective and fast fabrication processes.