Flow vorticity colored by velocity in the vicinity of the LAGOON#2 tow bar.
Mach number = 0.23
Re_D= 1.541 x 10 (Reynolds number based on the wheel diameter D = 0.3 m)
Vortex shedding due to the flow over the tow bar can be observed. This leads to tonal noise generation.
The simulations are performed using ProLB, a software suite based on the lattice Boltzmann method (www.prolb-cfd.com).
For more details about the simulation, please check the following article:
A. Sengissen, J.-C. Giret, C. Coreixas, and J.-F. Boussuge. Simulations of LAGOON landing gear noise using Lattice Boltzmann solver. In 21st AIAA/CEAS Aeroacoustics Conference, AIAA Paper 2015-2993, Dallas, USA. June 22-26, 2015.
The LAGOON (LAnding-Gear nOise database for CAA validatiON) project is supported by Airbus and ONERA.