Liquid hydrogen (LH₂) is gaining momentum as a sustainable aviation fuel, but its cryogenic nature poses significant challenges for ground operations, particularly aircraft refuelling. This process is increasingly recognised as a potential bottleneck for operational efficiency, as it can significantly extend turnaround times. Although some recent studies have proposed assumptions about LH₂ refuelling rates, their conclusions vary widely, and detailed modelling efforts remain limited. This paper presents the second part of a two-part study that aims to improve understanding of the LH₂ refuelling by delivering a validated numerical modelling framework and practical insights to support the design of future LH₂-powered aircraft and their airport refuelling operations. Part 1 focused on developing and validating a thermodynamic model that captures key physical phenomena such as heat transfer and droplet dynamics. The model was validated against experimental data from the LH₂ no-vent filling tests to demonstrate its accuracy in predicting relevant physical processes. In Part 2, the validated model is applied to a representative case study based on the Airbus ZEROe Turboprop concept. The objective is to quantify the refuelling time and hydrogen venting under realistic conditions. The simulation results indicate a refuelling time of approximately 19, min and ventilation losses of 36.7, kg, corresponding to approximately 2. 2 % of the total transferred LH₂ mass. Although the duration of refuelling exceeds that of current kerosene-powered aircraft such as the Bombardier Q400, the overall turnaround time remains feasible if the LH₂ refuelling process is carried out in parallel with other ground operations, subject to safety protocols. These findings challenge simplified assumptions in the previous literature and provide physics-based insight to support the design of safe and efficient LH₂ fuelling procedures and infrastructure for future zero-emission aviation.

Liquid hydrogen (LH₂) is a promising candidate for zero emission aviation, but its cryogenic properties make the refuelling process fundamentally different from that of conventional jet fuels. Although previous studies have addressed LH₂ storage and system integration, detailed modelling of the refuelling process remains limited. This paper presents the first part of a two-part study focused on simulation of the refuelling process for an LH₂-powered commercial aircraft. An existing tank model is substantially modified to more accurately capture relevant physical phenomena, including heat transfer and droplet dynamics during top-fill spray injection. Newly available experimental data on LH₂ no-vent filling enables direct validation of the model under conditions that match the experimental setup. A sensitivity analysis identifies the most influential parameters that affect model precision, including loss coefficient, droplet diameter, radiative heat ingress, and vent-closing pressure. The validated model forms the basis for Part 2 of this study, in which it is applied to a representative LH₂-powered commercial aircraft to simulate refuelling times, quantify venting losses, and assess the impact of key operational settings. These results support the design of efficient LH₂ refuelling systems for future aircraft and airport infrastructure.