Advertisement

Aircraft noise generation and assessment

A flight demonstration for airframe noise reduction technology
  • Kazuomi YamamotoEmail author
  • Kenji Hayama
  • Toshiyuki Kumada
  • Kensuke Hayashi
Original Paper
  • 23 Downloads

Abstract

This article overviews activities and results for an initial flight demonstration of a project, FQUROH, to develop and mature airframe noise reduction technologies. The project aims to demonstrate technologies for reducing airframe noise through three flight tests using aircraft with modified high-lift devices and landing gear. It intends to verify the design methods that utilize advanced computational fluid dynamics (CFD) and the feasibility of practical noise reduction concepts. The main purposes of the initial demonstration using a JAXA’s research aircraft in 2016 were to establish the processes for flight testing, including modification of the aircraft and experimental procedures, as well as to evaluate preliminary noise reduction designs. In the design process, noise reduction concepts for the flap and main landing gear were successfully applied to the actual complex geometries of the aircraft using advanced CFD, and the noise reduction effects were confirmed with noise measurements in wind tunnel tests. Based on the designs, the flap and main landing gear modifications were manufactured and installed on the aircraft. The flight demonstration campaign was successfully carried out with 177 noise source measurements, and encouraging results were obtained that show the feasibility of the noise reduction design method.

Keywords

Airframe noise Noise reduction Flight test 

Abbreviations

SPL

Sound pressure level, (dB)

PSD

Power spectral density, (dB/Hz)

PNL

Perceived noise level, (dB)

dB[A]

A-weighted decibel

Notes

Acknowledgements

The results presented here are due to the efforts of all project team members from JAXA, Kawasaki Heavy Industries, Sumitomo Precision Products and Mitsubishi Aircraft Corporation under the FQUROH collaboration framework. The Cessna Aircraft Company of Textron Aviation generously supported our work by providing the engineering data on our research aircraft, and Diamond Air Service, Calspan and Sumitomo Precision Products made extensive contributions to the aircraft modification works. We would like to express our gratitude to the Japan Civil Aviation Bureau, the administrative office of Noto Airport, the Japan Aviation Academy, and Wajima city. We also express our appreciation to Dr. Patricio A. Ravetta of AVEC for supporting the beamforming analysis software. We would also like to acknowledge the support of IHI Aerospace Engineering, the Kobayashi Institute of Physical Research, and the Propulsion Research Unit of JAXA for noise measurements, as well as the Flight Research Unit of JAXA and Aero Asahi Corporation in operating the aircraft.

References

  1. 1.
    Dobrzynski, W.: Almost 40 years of airframe noise research: what did we achieve? J. Aircr. 47(2), 353–367 (2010)CrossRefGoogle Scholar
  2. 2.
    Piet, J.-F., Chow, L.C., Laporte, F., Remy, H.: Flight test investigation of high-lift devices and landing gear modifications to achieve airframe noise reduction. In: ECCOMAS 2004 Conference, Jyvaskyla, Finland, July (2004)Google Scholar
  3. 3.
    Elkoby, R., et al.: Airframe noise test results from the QTD II flight test program. AIAA Paper 2007–3457 (2007)Google Scholar
  4. 4.
    Lockard, D.P., Choudhari, M.M.: The influence of realistic reynolds numbers on slat noise simulations. AIAA Paper 2012–2101 (2012)Google Scholar
  5. 5.
    Lockard, D.P., Choudhari, M.M., Buning, P.G.: Influence of spanwise boundary conditions on slat noise simulations. AIAA Paper 2015–3136 (2015)Google Scholar
  6. 6.
    Terracol, M., Manoha, E.: Wall-resolved large eddy simulation of a high-lift airfoil: detailed flow analysis and noise generation study. AIAA Paper 2014–3050 (2014)Google Scholar
  7. 7.
    Khorrami, M.R., Mineck, R.E.: Towards full aircraft airframe noise prediction: detached eddy simulations. AIAA Paper 2014–2480 (2014)Google Scholar
  8. 8.
    Khorrami, M.R., Fares, E., Casalinoand, D.: Towards full aircraft airframe noise prediction: lattice Boltzmann simulations. AIAA Paper 2014–2481 (2014)Google Scholar
  9. 9.
    44th AIAA Workshop on Benchmark Problems for Airframe Noise Computations (BANC-IV). https://info.aiaa.org/tac/ASG/FDTC/DG/BECAN_files_/BANCIV.htm. Accessed 27 Apr 2016
  10. 10.
    Yokokawa, Y., et al.: A far-field noise and near-field unsteadiness of a simplified high-lift-configuration model (Flap-edge). AIAA Paper 2009–283 (2009)Google Scholar
  11. 11.
    Imamura, T., et al.: A far-field noise and near-field unsteadiness of a simplified high-lift-configuration model (Slat). AIAA Paper 2009–1239 (2009)Google Scholar
  12. 12.
    Yokokawa, Y., et al.: Noise generation characteristics of a high-lift swept and tapered wing model. AIAA Paper 2013–2062 (2013)Google Scholar
  13. 13.
    Murayama, M., et al.: Numerical investigation on change of airframe noise by flap side-edge shape. AIAA Paper 2013–2067 (2013)Google Scholar
  14. 14.
    Yokokawa, Y., et al.: Experimental study on noise generation of a two-wheel main landing gear. AIAA Paper 2010–3973 (2010)Google Scholar
  15. 15.
    Murayama, M., et al.: Computational and experimental study on noise generation from tire-axle regions of a two-wheel main landing gear. AIAA Paper 2012–2279 (2012)Google Scholar
  16. 16.
    Takaishi, T., et al.: Flyover array measurements with JAXA flying test bed ‘Hisho’. AIAA Paper 2016–2710 (2016)Google Scholar
  17. 17.
    Murayama, M., et al.: Airframe noise reduction of flap side-edge using vortex generators. AIAA Paper 2017–4030 (2017)Google Scholar
  18. 18.
    Isotani, K.K., et al.: An aerodynamic noise reduction study for airframe noise from flap tips. AIAA Paper 2013–2064 (2013)Google Scholar
  19. 19.
    Murayama, M., et al.: Noise reduction design for flap side edges toward FQUROH flight demonstration. AIAA Paper 2017–4031 (2017)Google Scholar
  20. 20.
    RTRI’s Large-Scale Low-Noise Wind Tunnel. http://www.rtri.or.jp/rd/maibara-wt/English/index.html. Accessed 27 Apr 2016
  21. 21.
    Yokokawa, Y., et al.: Acoustic wind tunnel test with 18% scale Half-span model toward FQUROH flight demonstration. AIAA Paper 2017–4032 (2017)Google Scholar
  22. 22.
    Ito, Y., et al.: High-fidelity aerodynamic analysis of aircraft in various configurations with MEGG3D. AIAA Paper 2017–3804 (2017)Google Scholar
  23. 23.
    Ito, T., et al.: Aerodynamic/aeroacoustic testing in anechoic closed test sections of low-speed wind tunnels. AIAA Paper 2010–3750 (2010)Google Scholar
  24. 24.
    Takaishi, T., et al.: Noise reduction design for landing gear toward FQUROH flight demonstration. AIAA Paper 2017–4033 (2017)Google Scholar
  25. 25.
    Funabiki, K., Iijima, T., Nojima, T.: Method of trajectory generation for perspective flight-path display in estimated wind condition. J. Aerosp. Inf. Syst. 10(5), 240–249 (2013)Google Scholar

Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2019

Authors and Affiliations

  1. 1.Japan Aerospace Exploration AgencyChofu, TokyoJapan
  2. 2.Aerospace Systems Company, Kawasaki Heavy Industries, Ltd.Kakamigahara, GifuJapan
  3. 3.Sumitomo Precision Products, Co., Ltd.Amagasaki, HyogoJapan
  4. 4.Mitsubishi Aircraft CorporationNishikasugai-gun, AichiJapan

Personalised recommendations