FQUROH: a Flight Demonstration Project for Airframe Noise Reduction Technology - Concept and Current Status

22nd AIAA/CEAS Aeroacoustics Conference ◽

10.2514/6.2016-2709 ◽

2016 ◽

Cited By ~ 9

Author(s):

Kazuomi Yamamoto ◽

Kenji Hayama ◽

Toshiyuki Kumada ◽

Kensuke Hayashi

Keyword(s):

Noise Reduction ◽

Demonstration Project ◽

Current Status ◽

Airframe Noise

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FQUROH: A Flight Demonstration Project for Airframe Noise Reduction Technology - the 1st Flight Demonstration

23rd AIAA/CEAS Aeroacoustics Conference ◽

10.2514/6.2017-4029 ◽

2017 ◽

Cited By ~ 8

Author(s):

Kazuomi Yamamoto ◽

Takehisa Takaishi ◽

Mitsuhiro Murayama ◽

Yuzuru Yokokawa ◽

Yasushi Ito ◽

...

Keyword(s):

Noise Reduction ◽

Demonstration Project ◽

Airframe Noise

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FQUROH: A Flight Demonstration Project for Airframe Noise Reduction Technology – the 2nd Flight Demonstration

2018 AIAA/CEAS Aeroacoustics Conference ◽

10.2514/6.2018-4087 ◽

2018 ◽

Cited By ~ 6

Author(s):

Kazuomi Yamamoto ◽

Takehisa Takaishi ◽

Mitsuhiro Murayama ◽

Yuzuru Yokokawa ◽

Yasushi Ito ◽

...

Keyword(s):

Noise Reduction ◽

Demonstration Project ◽

Airframe Noise

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Trailing-edge noise reduction of a wing by a surface modification

INTER-NOISE and NOISE-CON Congress and Conference Proceedings ◽

10.3397/in-2021-2326 ◽

2021 ◽

Vol 263 (3) ◽

pp. 3194-3201

Author(s):

Varun Bharadwaj Ananthan ◽

R.A.D. Akkermans ◽

Dragan Kozulovic

Keyword(s):

Noise Reduction ◽

Stochastic Approach ◽

Slight Reduction ◽

Noise Sources ◽

Trailing Edge ◽

Sound Sources ◽

Airframe Noise ◽

Trailing Edge Noise ◽

Random Particle ◽

Noise Production

There is an increased emphasis on reducing airframe noise in the last decades. Airframe noise is sound generated by the interaction of a turbulent flow with the aircraft geometry, and significantly contributes to the overall noise production during the landing phase. One examples of airframe noise is the noise generated at a wing's trailing edge, i.e., trailing-edge noise. In this contribution, we numerically explore the local application of riblets for the purpose of trailing-edge noise reduction. Two configurations are studied: i) a clean NACA0012 wing section as a reference, and ii) the same configuration with riblets installed at the wing's aft part. The numerical investigation follows a hybrid computational aeroacoustics approach, where the time-average flow is studied by means of RANS. Noise sources are generated by means of a stochastic approach called Fast Random Particle Mesh method. The results show a deceleration of the flow behind the riblets. Furthermore, the turbulent kinetic energy indicates increased unsteadiness behind the riblets which is shifted away from the wall due to the presence of the riblets. Lastly, the sound sources are investigated by means of the 3D Lamb-vector, which indicates a slight reduction in magnitude near the trailing edge.

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