qingkai wei, siyang zhong, xun huang · 2013. 8. 27. · supported by the national natural science...
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Contact Information
Low Noise Aviation Lab, Peking University
Phone: 010-6275 8538
Email: huangxun@pku.edu.cn
Web: www.coe.pku.edu.cn/faculty/huangxun
Results
Experiment SetupA microphone array is used in an anechoic wind tunnel
with an open test section (the speed accuracy is within
± 0.1 m/s , 0.55 m × 0.4 m ) to yield noise source
images and characterize noise source spectra for a white
pigeon.
Experimental evaluation of flow-induced noise
in level flight of the pigeon (Columba livia)
BackgroundThe popularity of air traffic has led to serious
environmental issues in which noise is the most
distinguished issue for passengers and communities local
to airports. The development of high bypass ratio aero-
engine has the main contributor of aircraft noise moving
to the airframe for some modern transport aircrafts. Past
trends in aircraft noise reduction show that those
asymptotic improvements in airframe design might fail to
achieve the increasingly stringent regulations and the
public expectations.
Aviation researchers have been inspired by bird flight to
develop various aeronautic technologies. Avian wing
geometry and kinematic and aerodynamic mechanisms
have been extensively studied previously, particularly for
pigeons. Avian flight noise, however, is still an open
question, partially due to the absence of appropriate
testing methods.
Qingkai WEI, Siyang ZHONG, Xun HUANGState Key Laboratory of Turbulence and Complex Systems,
Department of Aeronautics and Astronautics, Peking University
AimPigeon’s level flight noise source images and characterize
noise source spectra can be given with a new experiment
method, which is different from those flyover noise
measurements and isolated dummy wing noise
measurements.
Future Work
3D real-time sound visualization method;
PIV or fluctuating pressure measurement on the wing;
Fluid mechanism of flexible flapping wing noise.
Acknowledgements
We thank Zhengwu Chen at China Aerodynamic Research and Development Center for his
care of the animal and the assistance in conducting these experiments. The work was
supported by the National Natural Science Foundation of China (No. 11172007) and
Science Foundation of Aeronautics of China (No. 20101271004).
2nd International Retreat on Vortex Dynamics and Vorticity Aerodynamics, Shanghai, August 15-17.
Array performance. (a) the layout of sensors; (b) photo of PKU
Array; (c) the associated array pattern at 3 kHz; (d) the signal-to-
noise ratio of the array. The live pigeon test results and preceding results (AIAA 2012-2230).
The experimental efforts can be largely eased off using isolated
dummy bird wing. However, the experimental accuracy using an
isolated wing of deceased birds needs justifications. (AIAA 2012-
2230)
Array Experiment setup. (a) The diagram of the experimental setup;
(b) image of the pigeon during the level flight at 𝑈∞ = 15 m/s.
The fly-over experiments capture flight noise mechanisms with high
confidence. However, it is very difficult to achieve a satisfactory
signal-to-noise ratio in those field tests. (AIAA J, Vol. 49, No. 4,
2011)
Acoustic image by Conventional Beamforming of the level flight at
𝑈∞ = 15 m/s, where the imaging frequency is (a) 2 kHz, (b) 3 kHz,
(c) 4 kHz, (d) 5 kHz, (e) 6 kHz, and (f) 7 kHz. The maximal sound
pressure value of each panel is normalized to 0 dB .
Acoustic image by DAMAS of the level flight at 𝑈∞ = 15 m/s, where
the imaging frequency is (a) 2 kHz, (b) 3 kHz, (c) 4 kHz, (d) 5 kHz, (e)
6 kHz, and (f) 7 kHz. The maximal sound pressure value of each panel
is normalized to 0 dB .
Some acoustic images of the pigeon’s level flight noise at
𝑈∞ = 15 m/s are shown, in which dynamic range is
10 dB, suggesting good quality of the experiments.
Dominant noise sources are at wing tips, which agrees
with the work by Geyer et al. (AIAA 2012-2230).
Sound strength is slightly asymmetrical because it is
difficulty to maintain perfectly horizontal level flight.
The spectral waveform of the pigeon flight suggests a
slope of −20 dB/dec between 500 Hz and 5 kHz.
A quantitative comparison:
the normalized SPL waveforms are almost the same at
low and middle frequency ranges;
our experiment are lower by a couple of decibels at
very high frequencies beyond 10 kHz.
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