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Ray-tracing approach to calculate acoustic shielding by a flying wing airframe
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2007 (English)In: AIAA Journal, ISSN 0001-1452, E-ISSN 1533-385X, Vol. 45, no 5, 1080-1090 p.Article in journal (Refereed) Published
Abstract [en]

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

Place, publisher, year, edition, pages
2007. Vol. 45, no 5, 1080-1090 p.
National Category
Aerospace Engineering
URN: urn:nbn:se:kth:diva-39086DOI: 10.2514/1.26000ISI: 000246195000013ScopusID: 2-s2.0-34249284117OAI: diva2:440136
AIAA/CEAS 12th Aeroacoustics Conference Location: Cambridge, MA Date: MAY 08-10, 2006 Available from: 2011-09-12 Created: 2011-09-08 Last updated: 2011-09-12Bibliographically approved

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Sefi, Sandy
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Numerical Analysis and Computer Science, NADA
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