摘要: Turbulent Boundary Layer (TBL) is the main source of interior noise of business jets during cruise. Designing damping material to reduce interior noise with minimum mass is challenging and requires accurate prediction of TBL noise... 展开 Turbulent Boundary Layer (TBL) is the main source of interior noise of business jets during cruise. Designing damping material to reduce interior noise with minimum mass is challenging and requires accurate prediction of TBL noise and its propagation into aircraft cabin. The Dassault Aviation cabin noise computation process is based on Reynolds Averaged Navier-Stokes (RANS) computations to provide the turbulent scales as inputs to the in-house code based on the Lighthill-Powell theory for wall pressure fluctuations cross-correlation predictions. These results are used by a Finite Element Method (FEM) to compute the transfer function of the structure and the noise propagating in the cabin and the cockpit. Measurements at low speed were conducted at the S2A wind tunnel on a full scale Falcon limited to the fore fuselage to validate the computational chain during the CANOBLE Clean Sky 2 project. Specific instrumentation was manufactured for the wall pressure measurements. The comparisons of the aeroacoustic measurements with the predictions show good agreements at 30m/s and 45m/s on the wall pressure fluctuations cross-correlation. Measurement at higher velocities are not reliable because of the saturation of the antenna. A better agreement is observed at very low flow velocity because of the high sensitivity of the model to two main aerodynamic data: the RMS velocity in the flow direction and the dissipation energy. The latter is particularly difficult to estimate close to the wall and can very significantly differ from a turbulence model to another leading to considerable deviations on the Power Spectral Density. 收起