Comparative Assessment of Aircraft System Noise Simulation
| Autor: | Jason C. June, Laurent Sanders, Lothar Bertsch, Mathieu Lorteau, Russell H. Thomas, Ian A. Clark, Ingrid LeGriffon |
|---|---|
| Přispěvatelé: | German Aerospace Center (DLR), DAAA, ONERA, Université Paris-Saclay [Châtillon], ONERA-Université Paris-Saclay, NASA Langley Research Center [Hampton] (LaRC) |
| Jazyk: | angličtina |
| Rok vydání: | 2021 |
| Předmět: |
Aircraft noise
Computer science Acoustics Aerospace Engineering Wing configuration 02 engineering and technology COMMUNITY NOISE benchmark test 01 natural sciences 7. Clean energy ACOUSTIC SHIELDING 010305 fluids & plasmas [SPI]Engineering Sciences [physics] 0203 mechanical engineering aircraft noise simulation 0103 physical sciences aircraft noise simulation working group (ANSWr) [CHIM]Chemical Sciences [INFO]Computer Science [cs] [MATH]Mathematics [math] Sound pressure [PHYS]Physics [physics] 020301 aerospace & aeronautics BENCHMARK CARMEN Noise PANAM Acoustic propagation ANOPP |
| Zdroj: | Journal of Aircraft Journal of Aircraft, American Institute of Aeronautics and Astronautics, 2021, pp.1-18. ⟨10.2514/1.C036124⟩ |
| ISSN: | 0021-8669 |
| Popis: | International audience; The Aircraft Noise Simulation Working Group (ANSWr) was established by DLR, ONERA, and NASA to compare simulation tools, establish guidelines for noise prediction, and assess uncertainties associated with the simulation. A benchmark test was initiated, and initial results for a reference and a low-noise vehicle are discussed. The reference aircraft is a conventional tube-and-wing configuration with the engines installed under the wings. The low-noise variant features a high wing design with engines mounted above the wing and fuselage junction. Simulations are performed for both departure and approach conditions, and the results obtained with the different system noise prediction tools are compared. For the reference aircraft, the overall agreement is good among the three predictions. Maximum A-weighted sound pressure levels received on the ground agree within 3–4 dB. For the low-noise vehicle, the comparison of the computed results focuses mainly on the acoustic shielding calculations, as well as on the noise source components. Considering these shielding effects, all three prediction methods show remarkable good agreement, with differences in maximum A-weighted sound pressure level typically lower than 4 dB. In conclusion, the results are quite promising. Despite simulation assumptions made to assist in the comparison, this work is a first and a positive step toward the development of a reliable and comprehensive comparison of these three aircraft noise simulation tools. |
| Databáze: | OpenAIRE |
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