Ingeniería Mecánica · 2025

Simulation and analysis of the drag coefficient in the simplified representative aircraft model based on the Baron G58 due to the integration of type IV hydrogen tanks

This study evaluates the impact on the drag coefficient produced by the integration of Type IV hydrogen tanks in a simplified representative aircraft model based on the Baron G58. Using parametric simulations in OpenVSP, the drag coefficient was analyzed for different tank geometries and installation locations: top of the fuselage, rear fuselage section, and under the wings. In addition, key design parameters were determined, including gravimetric density, storage volume, and the available hydrogen energy for operating pressures of 350, 700, and 1000 bar. The results confirm that both tank geometry and installation location play a decisive role in aerodynamic efficiency. The cylindrical tank installed in the rear fuselage achieved the lowest drag coefficient (≈ 0.0188 at 184 KTAS), while the cylindrical configuration on top of the fuselage achieved the highest gravimetric density (≈ 6 % at 350 bar). These findings highlight the trade-off between storage efficiency and aerodynamic penalty and provide practical guidelines for the development of hydrogen propulsion systems in general aviation, supporting global efforts to decarbonize air transport.