The “silent aircraft” is in the form of a flying wing with a large wing planform and a propulsion system that is in the rear of the airframe with intakes on the upper surface of the wing. Thus a large part of the forward propagating from the intake ducts is expected to be shielded from observers on the ground by the wing. Acoustic effects can be calculated by solving an external acoustic scattering problem for a moving aircraft. In this, acoustic shielding effects of the silent aircraft airframe are quantified by a ray-tracing method. The dominant from the noise spectrum of the engines are sufficiently high for ray theory to yield accurate results. It is that, for low-Mach number homentropic flows, a condition satisfied approximately during takeoff and, the acoustic rays propagate in straight lines. Thus, from Fermat’s principle it is clear that classical optics and geometrical theory of diffraction solutions are applicable to this moving-body problem as. The total amount of acoustic shielding at an observer located in the shadow region is calculated by adding the from all the diffracted rays (edge-diffracted and creeping rays) and then subtracting the result from the field without the airframe. The three-dimensional ray-tracing solver is validated by comparing the solutions with analytical high-frequency asymptotic solutions for canonical shapes. Experiments on a-scale geometry have been conducted in an anechoic chamber to test the applicability of the ray-tracing. The results confirm the accuracy of the approach, which is then applied to a CAD representation of a silent aircraft design. As expected, the flying wing configuration provides very significant ground shielding(in excess of 10 dB at all locations) of a source above the airframe.
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Agarwal et al. (2007) studied this question.