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Acoustic shielding calculations were performed for a generic test object (NACA 0012) and two realistic aircraft configurations, an Unmanned Aerial Vehicle (UAV) and a Hybrid Wing Body (HWB), and compared with experimental data, where the monopole sound source was realized using laser pulses. The agreement between calculation and experiment is good. Due to wind tunnel size limits experimental data are often restricted to the acoustic nearfield and its usability for farfield shielding predictions must be assessed numerically. In the present paper, shielding patterns were defined and its evolution with increasing distance from the geometry was studied using a simple shifting and scaling procedure. For higher frequencies, a linear scaling of the patterns with increasing distance could be established.

Computation and Validation of Acoustic Shielding at Realistic Aircraft Configurations