Numerical And Experimental Aerodynamic Investigation Of A Micro-UAV For Flying On Mars
Résumé
This paper presents a numerical and experimental investigation of the aerodynamic characteristics of a vertical take-off and landing micro air vehicle designed to fly in the Martian atmosphere. Numerical tools are validated through experimental data from the literature where Martian conditions are replicated. An innovative airfoil is designed for the specific flying conditions of the Martian MAV, i.e. compressible and ultra-low Reynolds number flows. This airfoil is evaluated in different Reynolds and Mach number conditions using unsteady compressible laminar Navier-Stokes simulations. Single rotors and coaxial configurations are designed for different thrust constraints by optimizing the chord and twist distributions using a free wake lifting line method. Rotors are firstly evaluated numerically using Navier-Stokes simulations. To validate the simulations, the optimized configurations are tested experimentally in an evacuation chamber, recreating Martian atmosphere in terms of density and gas. Thrust and torque on each rotor are measured by a two-component set-up. Tests are performed up to transonic flow conditions at blade tip. Results are extrapolated to a suggested design for a Martian MAV.
Origine : Fichiers produits par l'(les) auteur(s)
Loading...