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  • Other Sources  (5)
  • 1975-1979  (5)
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  • 1
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    Asymmetry of a circular jet observed in near and far fields (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Turbulence intensity measurements were made in three different-size jets at various Mach numbers and the aerodynamic jet axis, defined as the locus of points in the flow at which the turbulence intensity is minimum, was determined. The deviations from the geometrical jet axis were on the order of 2-4% of the nozzle diameter, and the pure jet axis had the form of a helical wave. A similar asymmetry in the radiated noise was also noted. The measured circumferential distribution of rms fluctuating velocity signals confirmed the asymmetry of even a circular jet.
    Keywords: ACOUSTICS
    Type: AIAA Journal; 17; May 1979
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development status of rotary engine at Toyo Kogyo (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Progress in the development of rotary engines which use a thermal reactor as the primary part of the exhaust emission control system is reviewed. Possibilities of further improvements in fuel economy of future rotary engines are indicated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center The Rotary Combust. Engine; p 37-84
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    On an acoustic field generated by subsonic jet at low Reynolds numbers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An acoustic field generated by subsonic jets at low Reynolds numbers was investigated. This work is motivated by the need to increase the fundamental understanding of the jet noise generation mechanism which is essential to the development of further advanced techniques of noise suppression. The scope of this study consists of two major investigation. One is a study of large scale coherent structure in the jet turbulence, and the other is a study of the Reynolds number dependence of jet noise. With this in mind, extensive flow and acoustic measurements in low Reynolds number turbulent jets (8,930 less than or equal to M less than or equal to 220,000) were undertaken using miniature nozzles of the same configuration but different diameters at various exist Mach numbers (0.2 less than or equal to M less than or equal to 0.9).
    Keywords: ACOUSTICS
    Type: NASA-CR-156182 , PROJ-REPT-170
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Peak Strouhal frequency of subsonic jet noise as a function of Reynolds number (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental study of the narrowband spectra of radiated sound from subsonic jets is discussed. It is found that the acoustic field is Reynolds-number-dependent below a Reynolds number of about 200,000. This has important implications for the study of coherent structures as radiators of sound.
    Keywords: ACOUSTICS
    Type: AIAA PAPER 79-1525 , American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference; Jul 23, 1979 - Jul 25, 1979; Williamsburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Peak Strouhal frequency of subsonic jet noise as a function of Reynolds number (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The narrowband spectral characteristics of the acoustic field generated by subsonic jets at low Reynolds numbers were studied in terms of a dimensionless power spectral density. It was found that the variation of the sound magnitude of the spectrum is an increasing function of the Reynolds number. The maximum level of the spectrum is not a linear function of the Reynolds number. The spectra are insensitive to Reynolds number above a critical value of about 100,000. Up to Reynolds number of this magnitude, the peak Strouhal frequency observed at 30 deg emission angle is identical with that at 90 deg for any exit Mach number. At higher Reynolds number the peak Strouhal number increases with increasing emission angle. The peak Strouhal number was found to be about 0.2, which is in agreement with previous findings that a few discrete modes at a Strouhal number of around 0.2 in low Reynolds number supersonic jets are powerful noise generators.
    Keywords: ACOUSTICS
    Type: AIAA Journal; 17; May 1979
    Format: text
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    NASA TECHNICAL REPORTS
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