Aerodynamic Flow Simulation of a Rudimentary Landing Gear Using PANS and LES

Abstract: Aerodynamic flow past a four wheel rudimentary airplane landing gear issimulated using two different simulation methods. Partially - averaged Navier- Stokes (PANS) and Large Eddy Simulation (LES). The rudimentary landinggear was specially designed for wind tunnel testing and CFD and is a ”steppingstone” case within the ATAAC project, an international project that aims toimprove CFD methods for flows relevant to todays aeronautical industry. Inthis study, PANS provides a seamless transition from k - ζ turbulence modeland Direct Numerical Simulation (DNS) based on the unresolved to total kineticenergy ratio (fk) and the unresolved to total dissipation ratio (fǫ). Thesimulation results are compared with available experimental data. PANS appearsto perform better than LES on the mesh used for this study. LES predictsfalse separation on the front wheel outboard sides whereas PANS correctly predictsattached flow. The computational mesh is generated in ICEM CFD andall simulations are performed with AVL FIRE.