Fixed-wing aircraft are particularly attractive for Mars surface exploration, but Martian low-density atmosphere poses several issues to airfoil aerodynamic design. In this framework, the paper deals with an optimization procedure aimed at maximize the aerodynamic efficiency of Low-Reynolds airfoils. The design procedure embeds airfoil parameterization, aerodynamic computation, and optimization algorithm for a maximum efficiency objective at two Reynolds. Two airfoil parameterization models are developed and adopted within the design optimization. The XFoil solver is considered to address airfoil aerodynamics; while its optimal shape is generated with a genetic algorithm to simulate a cruising condition. Design optimization developed two different airfoils with maximum lift-to-drag equal to 10.4 and 16.4. Aerodynamic performances of these wing sections are discussed in the work. Optimal airfoils pointed out that maximization of aerodynamic efficiency is associated to both a thickness reduction and a curvature increase of the aeroshape. Finally, aerodynamics of the optimal airfoils are also investigated with computational fluid dynamics simulations.
Aerodynamic optimization of airfoils shape for atmospheric flight on Mars planet
Iuspa L.;Pezzella G.;Viviani A.
2023
Abstract
Fixed-wing aircraft are particularly attractive for Mars surface exploration, but Martian low-density atmosphere poses several issues to airfoil aerodynamic design. In this framework, the paper deals with an optimization procedure aimed at maximize the aerodynamic efficiency of Low-Reynolds airfoils. The design procedure embeds airfoil parameterization, aerodynamic computation, and optimization algorithm for a maximum efficiency objective at two Reynolds. Two airfoil parameterization models are developed and adopted within the design optimization. The XFoil solver is considered to address airfoil aerodynamics; while its optimal shape is generated with a genetic algorithm to simulate a cruising condition. Design optimization developed two different airfoils with maximum lift-to-drag equal to 10.4 and 16.4. Aerodynamic performances of these wing sections are discussed in the work. Optimal airfoils pointed out that maximization of aerodynamic efficiency is associated to both a thickness reduction and a curvature increase of the aeroshape. Finally, aerodynamics of the optimal airfoils are also investigated with computational fluid dynamics simulations.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
