Simulation of a Generic Two-Wheel Nose Landing Gear Using High-order Finite Difference Schemes

Abstract

Aerodynamic noise from a generic two-wheel landing gear model is predicted by a CFD/FW-H hybrid approach. The unsteady flow field is computed by using a compressible Navier-Stokes solver based on high-order finite difference schemes and a fully structured grid. The calculated time history of the surface data is used in a FW-H solver to predict the far field noise levels. Both aerodynamic and aeroacoustic results are compared with wind tunnel measurements and are found in good agreement. Individual contributions from three components, i.e. wheels, axle and strut of the landing gear model are also investigated to identify the major noise source component. It is found that wheels are the dominant noise source in general. Strong vortex shedding from the axle is the second major contributor to landing gear noise. This work is part of Airbus LAGOON (landing gear noise database for CAA validation) program with the general purpose of evaluating up-to-date CFD/CAA and experimental techniques for airframe noise prediction (see AIAA Paper 2008-2816 by Manoha, Bulte and Caruelle, and AIAA Paper 2009-3277 by Manoha, Bulte, Ciobaca and Caruelle).