On the sensitivity of sound power radiated by aircraft panels to turbulent boundary layer parameters

Abstract The objective of the present study is to investigate and quantify how sensitive the response of an aircraft panel is to the change of the turbulent flow parameters. Several empirical models currently exist that provide the turbulent boundary layer wall pressure cross spectrum. These wall pressure cross spectrum models are usually dependent on four parameters: the reference power spectrum, the flow convective velocity, and the coherence lengths in streamwise and spanwise directions. All the proposed models provide different predictions for the wall pressure cross spectrum. Also, real flow conditions over aircraft do not conform to the ideal behavior of the turbulent boundary layer pressure predicted by the models. In this context, the questions that this work aims to explore are “What is the impact of different wall pressure estimates in the radiated sound power?” and “What is the effect of the range of possible flow conditions on the radiated sound power?”. For that objective, data from flight tests and estimates provided by the empirical models are used to predict radiated sound power, and the results are compared. A sensitivity analysis is performed and the relative contribution of each boundary layer parameter to the radiated sound power is obtained.

[1]  Wayne A. Strawderman,et al.  Turbulent‐Flow‐Excited Vibration of a Simply Supported, Rectangular Flat Plate , 1969 .

[2]  D. Chase.  Modeling the wavevector-frequency spectrum of turbulent boundary layer wall pressure , 1980 .

[3]  Fernando Lau,et al.  Prediction of flow-induced noise in transport vehicles: development and validation of a coupled structural - Acoustic analytical framework , 2009 .

[4]  Robert Rackl,et al.  Modeling of Turbulent Boundary Layer Surface Pressure Fluctuation Auto and Cross Spectra - Verification and Adjustments Based on TU-144LL Data , 2005 .

[5]  D. Chase.  The character of the turbulent wall pressure spectrum at subconvective wavenumbers and a suggested comprehensive model , 1987 .

[6]  Dwight E. Bishop.  Cruise Flight Noise Levels in a Turbojet Transport Airplane , 1961 .

[7]  H. G. Davies.  Sound from Turbulent‐Boundary‐Layer‐Excited Panels , 1969 .

[8]  L. Maestrello.  Radiation from and panel response to a supersonic turbulent boundary layer , 1969 .

[9]  Daniel L. Palumbo,et al.  The Influence of Boundary Layer Parameters on Interior Noise , 2012 .

[10]  Cédric Maury,et al.  A WAVENUMBER APPROACH TO MODELLING THE RESPONSE OF A RANDOMLY EXCITED PANEL, PART II: APPLICATION TO AIRCRAFT PANELS EXCITED BY A TURBULENT BOUNDARY LAYER , 2002 .

[11]  S. F. Al-Fahed,et al.  The behavior of the skin-friction coefficient of a turbulent boundary layer flow over a flat plate with differently configured transverse square grooves , 2005 .

[12]  C. Wallace.  Radiation Resistance of a Rectangular Panel , 1972 .

[13]  Bilong Liu,et al.  Noise radiation of aircraft panels subjected to boundary layer pressure fluctuations , 2008 .

[14]  Wr Graham,et al.  A comparison of models for the wavenumber-frequency spectrum of turbulent boundary layer pressures (Reprinted from Proceedings of First CEAS/AIAA Aeroacoustics Conference, June, 1995) , 1997 .

[15]  W. V. Bhat.  Flight test measurement of exterior turbulent boundary layer pressure fluctuations on Boeing model 737 airplane , 1971 .

[16]  J. F. Wilby,et al.  Vibration measurements of an airplane fuselage structure I. Turbulent boundary layer excitation , 1972 .

[17]  Bilong Liu,et al.  Sound transmission through curved aircraft panels with stringer and ring frame attachments , 2007 .

[18]  L. Rayleigh,et al.  The theory of sound , 1894 .

[19]  Daniel L. Palumbo.  Measurement of the Correlation and Coherence Lengths in Boundary Layer Flight Data , 2013 .

[20]  M. Bull.  WALL-PRESSURE FLUCTUATIONS BENEATH TURBULENT BOUNDARY LAYERS: SOME REFLECTIONS ON FORTY YEARS OF RESEARCH , 1996 .

[21]  Bilong Liu,et al.  Influence of overpressure on sound transmission through curved panels , 2007 .

[22]  Brian Bingham,et al.  COMPARISON OF STRUCTURAL–ACOUSTIC CONTROL DESIGNS ON AN ACTIVE COMPOSITE PANEL , 2001 .

[23]  J. F. Wilby,et al.  Interior noise radiated by an airplane fuselage subjected to turbulent boundary layer excitation and evaluation of noise reduction treatments , 1971 .

[24]  S. Hambric,et al.  Comparison of semi-empirical models for turbulent boundary layer wall pressure spectra , 2009 .

[25]  G. Corcos.  Resolution of Pressure in Turbulence , 1963 .

[26]  Lucio M. Maestrello,et al.  Measurement of noise radiated by boundary layer excited panels , 1965 .

[27]  J. F. Wilby.  AIRCRAFT INTERIOR NOISE , 1996 .

[28]  Robert L. Clark,et al.  AEROELASTIC STRUCTURAL ACOUSTIC COUPLING : IMPLICATIONS ON THE CONTROL OF TURBULENT BOUNDARY-LAYER NOISE TRANSMISSION , 1997 .

[29]  D. A. Bies,et al.  A review of flight and wind tunnel measurements of boundary layer pressure fluctuations and induced structural response , 1966 .

[30]  G. Corcos.  The structure of the turbulent pressure field in boundary-layer flows , 1964, Journal of Fluid Mechanics.

[31]  Cédric Maury,et al.  Active Control of the Flow-Induced Noise Transmitted Through a Panel , 2001 .

[32]  J. F. Wilby,et al.  Vibration measurements of an airplane fuselage structure II. Jet noise excitation , 1972 .