This paper presents a wing design for the APUS i-2 concept hydrogen fuel cell aircraft that meets design requirements for hydrogen storage, lift and drag characteristics and manoeuvrability. Airfoil polars and lift distribution calculations were produced on a split-flap wing using XFOIL and Athena Vortex Lattice (AVL) software. Computer results were used to modify the wing design until an optimal airfoil shape was developed for both cruise and landing conditions. A model of the airfoil design was then manufactured for wind tunnel testing at TU Dresden to produce experimental lift and drag results, which were later compared to the theoretical data. The results collected throughout the experimental campaigns were extrapolated to a finite wing using numerical lifting line methods to fully model the final wing design´s aerodynamic behaviour on the i-2 aircraft. Finally, the aircraft´s manoeuvrability with the given ailerons and induced drag reduction efforts were investigated.