Validation of a New Solver based on the Vortex Particle Method for Wings, Propellers and Rotors

Abstract

The Vortex Particle Method (VPM) represents continuous, incompressible, unsteady, viscous flows through the use of singular, independent particles represented by small concentration of vorticity. This method is convenient for simulating vortex reconnections in the wake as well as flow mixing. This study aims to provide a mid-fidelity aerodynamic solver based on the VPM. Coupled with a Lifting Line (LL), the VPM-LL solver predicts an accurate flow solution of a lifting body in an unbounded freestream, with a significantly reduced computational cost compared to classical CFD solvers. After introducing the VPM, its implementation is detailed. The coupling with the LL is explained and validated on two wings, an axial propeller and a drone rotor, through the comparison of CFD, experimental and analytical results. A quadrotor drone from the GARTEUR Action Group 25 is studied and compared to the experimental data from DLR and numerical results from DLR and ONERA.