Optimized Airfoil Design for Aerial Flight Vehicles in Low-Reynolds Flight

This invention, developed under the Rotor Optimization for the Advancement of Mars eXploration (ROAMX) project, provides a method for optimizing airfoil geometries for aerial flight vehicles generally, and can also specifically optimize airfoil geometries for operating in Martian or other low Reynolds number environments. The method introduces a new “ROAMX parameterization” that defines geometric constraints, such as camber node count and the number and order of Bézier curve segments, to generate candidate airfoil shapes. A genetic algorithm evaluates these shapes against multiple objectives and iteratively selects the best-performing designs, converging on a Pareto-optimal front. This enables simultaneous optimization of metrics such as maximizing lift and minimizing drag. Using the ROAMX 1301 parameterization, the method produced an airfoil with lift to drag ratio improvements of up to 42% over the outboard airfoil used on the Mars Helicopter Ingenuity, representing a significant performance gain. The success of the Mars Helicopter Ingenuity has inspired efforts to improve fundamental understanding of compressible, low Reynolds number aerodynamics and wing/rotor performance, especially in atmospheres of very low densities. Studies have focused on optimizing unconventional airfoils, revealing significant possible advancements in sectional aerodynamic airfoil performance. Ames Research Center has developed a technology that relates generally to multi-objective optimization and, more particularly, to methods and systems for producing efficient airfoil geometries for use in aerial flight vehicles in low Reynolds conditions. The invention, developed under the Rotor Optimization for the Advancement of Mars eXploration (ROAMX) project, provides a method for optimizing airfoil geometries for aerial flight vehicles in general, and also supports airfoil geometries specifically for operating in Martian or other Low Reynolds number environments.