Abstract
The purpose of this paper is the computational investigation of unsteady flowfield related to the aeroacoustic generation around the landing gear designed by Japan Aerospace Exploration Agency (JAXA) and the difference of aeroacoustic noise level by changing component locations and shapes. The JAXA landing gear is constructed with complicated geometry components such as brake-caliper, torque link and wheel cap. The flowfeild around the landing gear is investigated by the Building-Cube Method (BCM). The BCM is a multiblock-structured Cartesian mesh flow solver. The present BCM uses the incompressible Navier-Stokes equation as governing equation, solved with the subgrid-scale (SGS) model as an unsteady turbulence model and the wall model. The aeroacoustic noise is investigated by the non-Compact Curle's equation, which is modified Curle's equation to be able to consider the size of landing gear and the uniform flow effect as the Doppler effect. In this paper, the difference of landing gear noise and unsteady flowfield are investigated with the change of torque link locations and wheel cap shapes by BCM and Non-compact Curle's equation . The result shows that the torque link position affects the flowfield around the main strut and wheel, which acts on the aeroaoustic noise. The wheel cap geometry also affects to the aeroacoustic noise.
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