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林 秀千人, Hayashi Hidechito, K. Yoshio, 好雄 児玉, 徹 深野, Fukano Tohru, Ikeda Masahiro, 昌浩 池田 (1995)
Relationship between Wake Vortex Formation and Discrete Frequency Noise in NACA BladesTransactions of the Japan Society of Mechanical Engineers. B, 61
H Hayashi, Y Kodama, Y Fukano, M Ikeda (1995)
Relationship between wake vortex formation and discrete frequency noise in NACA blades (in Japanese)Trans Jpn Soc Mech Eng, 61
By Arbey, J., Bataille (1983)
Noise generated by airfoil profiles placed in a uniform laminar flowJournal of Fluid Mechanics, 134
H. Kim, S. Lee, N. Fujisawa (2006)
Computation of unsteady flow and aerodynamic noise of NACA0018 airfoil using large-eddy simulationInternational Journal of Heat and Fluid Flow, 27
S. Tomimatsu, N. Fujisawa (2002)
Measurement of aerodynamic noise and unsteady flow field around a symmetrical airfoilJournal of Visualization, 5
M. Roger, S. Moreau (2004)
Broadband Self Noise from Loaded Fan BladesAIAA Journal, 42
J. Kompenhans, M. Raffel, L. Dieterle, T. Dewhirst, H. Vollmers, K. Ehrenfried, C. Willert, K. Pengel, C. Kähler, A. Schröder, O. Ronneberger (1999)
Particle image velocimetry in aerodynamics: Technology and applications in wind tunnelsJournal of Visualization, 2
C. Shih, L. Lourenço, A. Krothapalli (1995)
Investigation of flow at leading and trailing edges of pitching-up airfoilAIAA Journal, 33
S. Akishita (1986)
Tone-like noise from an isolated two dimensional airfoil
S. Wright (1975)
The acoustic spectrum of axial flow machinesJournal of Sound and Vibration, 45
E. Manoha, B. Troff, P. Sagaut (2000)
Trailing-Edge Noise Prediction Using Large-Eddy Simulation and Acoustic AnalogyAIAA Journal, 38
N. Fujisawa, G. Takeda (2003)
Flow control around a circular cylinder by internal acoustic excitationJournal of Fluids and Structures, 17
R. Longhouse (1977)
Vortex shedding noise of low tip speed, axial flow fansJournal of Sound and Vibration, 53
C. Tam (1974)
Discrete tones of isolated airfoilsJournal of the Acoustical Society of America, 55
N. Fujisawa, S. Tanahashi, K. Srinivas (2005)
Evaluation of pressure field and fluid forces on a circular cylinder with and without rotational oscillation using velocity data from PIV measurementMeasurement Science and Technology, 16
A. McAlpine, E. Nash, M. Lowson (1999)
On the Generation of Discrete Frequency Tones by the Flow around an AerofoilJournal of Sound and Vibration, 222
M. Howe (1978)
A review of the theory of trailing edge noiseJournal of Sound and Vibration, 61
N. Fujisawa, Y. Hashizume (2001)
An uncertainty analysis of temperature and velocity measured by a liquid crystal visualization techniqueMeasurement Science and Technology, 12
H. Kim, S. Lee, N. Fujisawa (2002)
A Study on Discrete Frequency Noise from a Symmetrical Airfoil in a Uniform Flow
E. Nash, M. Lowson, A. McAlpine (1999)
Boundary-layer instability noise on aerofoilsJournal of Fluid Mechanics, 382
Meng Wang, P. Moin (2000)
Computation of Trailing-Edge Flow and Noise Using Large-Eddy SimulationAIAA Journal, 38
RE Longhouse (1977)
Vortex shedding of low tip speed, axial flow fansJ Sound Vib, 53
Robert Paterson, P. Vogt, Martin Fink, C. Munch (1972)
Vortex Noise of Isolated AirfoilsJournal of Aircraft, 10
L. Lourenço (1989)
Particle Image Velocimetry, 9
The characteristics of tonal noise and the variations of flow structure around NACA0018 airfoil in a uniform flow are studied by means of simultaneous measurement of noise and velocity field by particle-image velocimetry to understand the generation mechanism of tonal noise. Measurements are made on the noise characteristics, the phase-averaged velocity field with respect to the noise signal, and the cross-correlation contour of velocity fluctuations and noise signal. These experimental results indicate that the tonal noise is generated from the periodic vortex structure on the pressure surface of the airfoil near the trailing edge of the airfoil. It is found that the vortex structure is highly correlated with the noise signal, which indicates the presence of noise-source distribution on the pressure surface. The vorticity distribution on the pressure surface breaks down near the trailing edge of the airfoil and forms a staggered vortex street in the wake of the airfoil.
Experiments in Fluids – Springer Journals
Published: Dec 20, 2005
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