The recent development of drones for very high altitudes or hybrid airships that generate aerodynamic lift in addition to the aerostatic lift typical of airships brought attention to the analysis and design of very low Reynolds number configurations. This work, in particular, focuses on the design issues of a propeller for this type of airship equipped with electric propulsion. The design and subsequent optimization of high-altitude propellers would require the use of very sophisticated numerical simulation tools to deal with the transition from laminar to turbulent flows and laminar bubbles, which would lead to a significant use of computational resources. Here, a simple and effective approach is presented. A family of airfoils is designed by adopting an optimization process based on a hierarchy of solvers of increasing fidelity, moving from an integral boundary layer coupled to a potential solver with compressibility correction to approaches based on the coupling of solvers of the Euler or Reynolds Averaged Navier-Stokes equations (RANS) coupled boundary layer with simple transition models, up to RANS solvers with transitional turbulence models such as \(\gamma \text{-Re }\,\theta \) . Once the 2D aerodynamics of the newly developed high-performance blade sectional airfoils are numerically calculated in the form of look-up tables, a classical inverse blade design method is applied, resulting in a baseline propeller geometry which is then further refined by means of exploration of the design space and optimization.