Item Details

Numerical Simulation of Noise Propagation in Jet Engine Ducts

by Kenneth J. Baumeister and Edward C. Bittner
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973.
Language
English
Series
NASA Technical Note
Summary
A finite difference formulation is presented which is useful in the study of acoustically treated inlet and exhaust ducts used in turbofan engines. The difference formulation can readily handle acoustic flow field complications, such as axial variations in wall impedance and cross-sectional area, that would occur in a sonic inlet. In formulating the difference solutions, the continuous acoustic field is lumped into a series of grid points spread uniformly throughout the field. At each point, the pressure is separated into its real and imaginary terms. Example solutions are presented for sound propagation in a one-dimensional straight hard-wall duct and in a two-dimensional straight soft-wall duct without steady flow.
Description
iii, 46 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Lewis Research Center.
  • Cover title.
  • Bibliography: p. 40-41.
Series Statement
NASA technical note ; NASA TN D-7339
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Numerical simulation of noise propagation in jet engine ducts c| by Kenneth J. Baumeister and Edward C. Bittner.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1973.
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    a| iii, 46 p. : b| ill. ; c| 27 cm.
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    0
      
    a| NASA technical note ; v| NASA TN D-7339
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    a| Prepared at Lewis Research Center.
    500
      
      
    a| Cover title.
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    a| Bibliography: p. 40-41.
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    a| A finite difference formulation is presented which is useful in the study of acoustically treated inlet and exhaust ducts used in turbofan engines. The difference formulation can readily handle acoustic flow field complications, such as axial variations in wall impedance and cross-sectional area, that would occur in a sonic inlet. In formulating the difference solutions, the continuous acoustic field is lumped into a series of grid points spread uniformly throughout the field. At each point, the pressure is separated into its real and imaginary terms. Example solutions are presented for sound propagation in a one-dimensional straight hard-wall duct and in a two-dimensional straight soft-wall duct without steady flow.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Airplanes x| Turbofan engines x| Noise x| Mathematical models.
    650
      
    0
    a| Airplanes x| Air ducts x| Noise x| Mathematical models.
    700
    1
      
    a| Bittner, Edward C.
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    1
      
    a| United States. b| National Aeronautics and Space Administration.
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    a| Lewis Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106885251 y| 1973 r| pd q| bib

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