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  • FLUID MECHANICS AND HEAT TRANSFER  (3)
  • 1
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    Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Transition data on sharp tip cones in two pilot low disturbance wind tunnels at Mach numbers of 3.5 and 5 were correlated in terms of noise parameters with data from several conventional wind tunnels and with data from supersonic flight tests on a transition cone. The noise parameters were developed to account for the large axial variations of the free stream noise and the very high frequency noise spectra that occurred in the low disturbance tunnels for some test conditions. The noise could be varied in these tunnels from high levels, approaching those in conventional tunnels, to extremely low levels. The correlations indicated that transition in the low disturbance tunnels was dominated by the local stream noise that was incident on the cone boundary layer unstream of the neutral stability point. The correlation results also suggested that high frequency components of the low disturbance tunnel noise spectra had significant effects on transition when the noise was incident on the boundary layer both upstream and downstream of the neutral stability point.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-2229 , NAS 1.60:2229 , L-15669
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation at Mach 3.5 into the effects of nozzle wall roughness on free stream pressure fluctuations and cone transition Reynolds numbers was conducted in the pilot low disturbance tunnel at the Langley Research Center. Nozzle wall roughness caused by either particle deposits or imperfections in surface finish increased free stream noise levels and reduced the transition Reynolds numbers on a cone mounted in the test rhombus.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-86389 , L-15903 , NAS 1.15:86389
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A small scale Mach 3.5 wind tunnel incorporating certain novel design features and intended for boundary-layer-transition research has been tested. The free stream noise intensities and spectral distributions were determined throughout the test section for several values of unit Reynolds number and for nozzle boundary layer bleed on and off. The boundary layer transition location on a slender cone and the response of this to changes in the noise environment were determined. Root mean square free stream noise levels ranged from less than one tenth up to values approaching those for conventional nozzles, with the lowest values prevailing at upstream locations within the nozzle. For low noise conditions, cone transition Reynolds numbers were in the range of those for free flight; whereas for high noise conditions, they were in the range of those in conventional tunnels.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-2180 , L-15610 , NAS 1.60:2180
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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