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  • 1
    Electronic Resource
    Electronic Resource
    The Physics of Supersonic Turbulent Boundary Layers (1994)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Fluid Mechanics 26 (1994), S. 287-319 
    Details
    ISSN: 0066-4189
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.fl.26.010194.001443
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  • 2
    Electronic Resource
    Electronic Resource
    The Response of Turbulent Boundary Layers to Sudden Perturbations (1985)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Fluid Mechanics 17 (1985), S. 321-358 
    Details
    ISSN: 0066-4189
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.fl.17.010185.001541
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  • 3
    Electronic Resource
    Electronic Resource
    Analysis of a rapidly distorted, supersonic, turbulent boundary layer (1989)
    New York, NY : American Institute of Physics (AIP)
    Physics of Fluids 1 (1989), S. 1855-1864 
    Details
    ISSN: 1089-7666
    Source: AIP Digital Archive
    Topics: Physics
    Notes: Rapid distortion concepts are used to calculate the evolution of turbulent stresses in the flow of a compressible boundary layer through a short region of concave curvature. Different models for the rapid part of strain were tested. For all models used, the calculations in the curved region agree well with experimental data. Downstream, however, the discrepancies between experiment and calculation increase, probably because of the increased importance of the mean shear and the nonlinear terms.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1063/1.857510
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  • 4
    Electronic Resource
    Electronic Resource
    A comparison of the turbulence structure of subsonic and supersonic boundary layers (1989)
    New York, NY : American Institute of Physics (AIP)
    Physics of Fluids 1 (1989), S. 1865-1875 
    Details
    ISSN: 1089-7666
    Source: AIP Digital Archive
    Topics: Physics
    Notes: A comparison of the turbulence structure of subsonic and supersonic boundary layers reveals that, despite broad similarities, significant differences exist. The length scales derived from space-time correlations indicate that the spanwise scales are almost identical but that the streamwise scales in the supersonic flow are about half the size of those in subsonic flow. The large-scale structures in the subsonic boundary layer appear to move slightly slower, and lean more toward the wall than those observed in supersonic flows, and their shear stress content is distributed differently among the four quadrants. These observations should have a strong impact on deriving turbulence models for high Reynolds number supersonic flows.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1063/1.857511
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  • 5
    Electronic Resource
    Electronic Resource
    Horseshoe vortex systems resulting from the interaction between a laminar boundary layer and a transverse jet (1995)
    [S.l.] : American Institute of Physics (AIP)
    Physics of Fluids 7 (1995), S. 153-158 
    Details
    ISSN: 1089-7666
    Source: AIP Digital Archive
    Topics: Physics
    Notes: The horseshoe vortex system resulting from the interaction between a laminar boundary layer and a round transverse jet was studied over a range of Reynolds numbers and velocity ratios using hydrogen bubble wire visualization in a water channel. The study shows that the horseshoe vortex system can be steady, oscillating, or coalescing, depending on the flow conditions. Topological concepts are used to interpret the observed flow patterns and compare these patterns with those observed and computed upstream of wall-mounted circular cylinders. The Strouhal numbers of the observed oscillating and coalescing systems agree reasonably well with those appearing in the literature for wall-mounted circular cylinders. The relationship between the unsteady horseshoe vortex motions and the unsteady vortex motions in the wake is studied for a velocity ratio of 4. Here it is shown that the oscillating regime occurs at the same frequency as the wake and the coalescing regime occurs at approximately double the frequency of the wake. The results indicate that the wake intermittently becomes coupled to the horseshoe vortex motions and that this occurs either at the horseshoe vortex frequency in the case of the oscillating system or a subharmonic in the case of the coalescing system. © 1995 American Institute of Physics.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1063/1.868736
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  • 6
    Electronic Resource
    Electronic Resource
    Constant temperature hot-wire anemometer practice in supersonic flows (1983)
    Springer
    Experiments in fluids 1 (1983), S. 83-92 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract The performance of a constant-temperature normal hotwire in a supersonic flow is critically examined. It is shown that this instrument is inherently unsuitable for measuring turbulent temperature correlations because of the highly non-linear response to temperature fluctuations, particularly at low overheat ratios. The instrument is therefore limited to measurements of mean and fluctuating mass-flow rates. Suitable calibration procedures. as well as the limits on spatial and temporal resolution are discussed. and corrections for mean stagnation temperature changes are suggested. The instrument was used to measure the mass-flow fluctuations in a zero pressure gradient Mach 2.9 turbulent boundary layer. A comparison with the available data suggests good agreement.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00266260
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  • 7
    Electronic Resource
    Electronic Resource
    Visualization of the structure of supersonic turbulent boundary layers (1995)
    Springer
    Experiments in fluids 18 (1995), S. 288-302 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract A series of flow visualizations has been performed on two flat-plate zero-pressure-gradient supersonic boundary layers. The two different boundary layers had moderate Mach numbers of 2.8 and 2.5 and Re θ's of 82, 000 and 25, 000 respectively. A number of new visualization techniques were applied. One was a variation of conventional schlieren employing “selective cut-off” at the knife edge plane. Motion pictures of the flow were generated with this technique. Droplet seeding was also used to mark the flow, and high speed movies were made to show structure evolution. Still pictures were also taken to show details within the large-scale motions. Finally, Rayleigh scattering was used to construct planar images of the flow. Together, these techniques provide detailed information regarding the character and kinematics of the large-scale motions appearing in boundary layers in supersonic flow. Using these data, in concert with existing hot-wire data, some suggestions are made regarding the characteristics of the “average” large-scale motion.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00195099
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  • 8
    Electronic Resource
    Electronic Resource
    The static response of a bowed inclined hot wire (1984)
    Springer
    Experiments in fluids 2 (1984), S. 183-187 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract The directional sensitivity of a bowed, inclined hot wire is investigated using a simple model for the convective heat transfer. The static response is analyzed for subsonic and supersonic flows. It is shown that the effects of both end conduction and wire bowing are greater in supersonic flow. Regardless of the Mach number, however, these two phenomena have distinctly different effects; end conduction appears to be responsible for reducing the nonlinearity of the response, whereas bowing increases the directional sensitivity. Comparison with the available data suggests that the analysis is useful for interpreting the experimental results.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00571862
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  • 9
    Electronic Resource
    Electronic Resource
    Constant temperature hot-wire anemometer practice in supersonic flows (1984)
    Springer
    Experiments in fluids 2 (1984), S. 33-41 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract The performance of a constant-temperature inclined hot-wire in a supersonic flow is critically examined. It is shown that empirical heat transfer correlations commonly used for calibrating hot wires in subsonic flow cannot be used when the flow is supersonic. Calibration and measurement procedures appropriate to supersonic flow are suggested, together with the possible limits on their validity. The instrument was used to measure the mass-weighted Reynolds shear stress $$\overline {\left( {\varrho u} \right)\prime v\prime } $$ in a zero pressure gradient Mach 2.9 turbulent boundary layer. A comparison with the available data suggests good agreement, as long as the normal Mach number remains supersonic under all conditions.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00266316
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  • 10
    Electronic Resource
    Electronic Resource
    Wall pressure fluctuations in the reattachment region of a supersonic free shear layer (1993)
    Springer
    Experiments in fluids 14 (1993), S. 10-16 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract A study was made of the wall pressure fluctuations in the reattachment region of a supersonic free shear layer. The free shear layer was formed by the separation of a Mach 2.9 turbulent boundary layer from a backward facing step. Reattachment occurred on a 20° ramp. By adjusting the position of the ramp, the base pressure at the step was set equal to the freestream pressure, and the free shear layer formed in the absence of any turning. An array of flush-mounted, miniature, high-frequency pressure transducers was used in the vicinity of the reattachment region to make multichannel measurements of the fluctuating wall pressure. Contrary to previous observations of this flow, the reattachment region was found to be highly unsteady, and the pressure fluctuations were found to be large. The overall behavior of the wall pressure loading is similar in scale and magnitude to the unsteadiness of the wall pressure field in compression ramp flows at the same Mach number. Rayleigh scattering was used to visualize the instantaneous shock structure in the streamwise and spanwise direction. Spanwise “wrinkles” on the order of half the boundary layer thickness were observed on the shock sheet.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00196982
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