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  • 1
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    Mean and fluctuating flow measurements of a fully-developed, non-adiabatic, hypersonic boundary layer (1975)
    Cambridge University Press
    Details
    Publication Date: 1975-07-29
    Description: Extensive boundary-layer measurements have been made on a cone-ogive-cylinder model at a free-stream MacH number of 7·0 and momentum-thickness Reynolds number of 8500. Mean flow transformations and calculated turbulence correlations are presented which are in good agreement with previous incompressible results. New quantitative turbulence measurements including measurements of the first higher moment and probability density of fluctuations in mass flow and total temperature in hypersonic flow are also presented. The higher moment and probability density data show that the characters of the fluctuation modes of the mass flow and total temperature are significantly different in the wall region and in the outer part of the boundary layer. These differences together with data on the turbulence scale and lifetime obtained from autocorrelation and space-time correlation measurements are discussed. © 1975, Cambridge University Press. All rights reserved.
    Print ISSN: 0022-1120
    Electronic ISSN: 1469-7645
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Cambridge University Press
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    PAPER CURRENT
  • 2
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    On the structure of hypersonic turbulent boundary layers (1972)
    Cambridge University Press
    Details
    Publication Date: 1972-06-27
    Description: Extensive hot-wire auto- and cross-correlation measurements obtained in a fully developed compressible turbulent boundary layer are presented. A tentative mechanism of turbulence production and growth in hypersonic flow suggested by these measurements is developed. This flow model is consistent with previous observations in incompressible flows. Detailed measurements of the mean properties of the hypersonic turbulent boundary layer are also presented and compared with results from various transformation and finite-difference prediction methods. It is shown that none of the theories predict all the properties of the hypersonic turbulent boundary layer and that additional measurements are needed to provide more adequate physics of turbulent processes for use in the various theories. © 1972, Cambridge University Press. All rights reserved.
    Print ISSN: 0022-1120
    Electronic ISSN: 1469-7645
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Cambridge University Press
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  • 3
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    Applications of dynamic measurement techniques to wind-tunnel testing (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The uses of laser Doppler velocimeter, hot wire, and surface hot film techniques in the study of turbulent flows are described, and data obtained in compressible flows are discussed. Applications are illustrated with measurements of wind tunnel freestream turbulence characteristics and with data obtained in transitional, turbulent, and separated shear flows. A new method which was developed for the study of time dependent and unsteady turbulent flows is also presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 571-588
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Skin-friction measurement at supersonic speeds (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Skin friction measurement in supersonic flows by thin film heated element method, describing thermal boundary layer properties
    Keywords: FLUID MECHANICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    New diagnostic technique for the study of turbulent boundary-layer separation (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Description of a diagnostic technique for determining the unsteady character of turbulent boundary-layer separation. The technique uses thin platinum films mounted flush with the model surface. Voltages from these films provide measurements related to the flow character above the film. For illustration, results obtained by this technique are presented for the interaction of a hypersonic shock wave and a turbulent boundary layer, with and without separation.
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 12; Oct. 197
    Format: text
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  • 6
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    On the structure of hypersonic turbulent boundary layers. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Extensive hot-wire auto- and cross-correlation measurements obtained in a fully developed compressible turbulent boundary layer are presented. A tentative mechanism of turbulence production and growth in hypersonic flow suggested by these measurements is developed. This flow model is consistent with previous observations in incompressible flows. Detailed measurements of the mean properties of the hypersonic turbulent boundary layer are also presented and compared with results from various transformation and finite-difference prediction methods. It is shown that none of the theories predict all the properties of the hypersonic turbulent boundary layer and that additional measurements are needed to provide more adequate physics of turbulent processes for use in the various theories.
    Keywords: FLUID MECHANICS
    Type: Journal of Fluid Mechanics; 53; June 27
    Format: text
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  • 7
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    Hypersonic transitional boundary layers. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Surface thin-film gages have been used to determine the extent of the transition region, intermittency distribution, and disturbance convection velocities in the boundary layer on a sharp 5-deg half angle cone at Mach 7.4 in the Ames 3.5-ft Hypersonic Wind Tunnel. In addition, extensive hot wire space-time correlation measurements have been obtained in the wind-tunnel freestream and in the transitional hypersonic boundary layer on a cone-ogive-cylinder in the same facility. Disturbance convection velocities have been obtained from the longitudinal cross correlation measurements as a function of fluctuation scale and distance from the wall. The results of normal cross correlation measurements are also discussed.
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 10; June 197
    Format: text
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  • 8
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    Turbulent properties of a compressible boundary layer. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Turbulent shear-stress, eddy-viscosity, mixing-length, heat-flux and Prandtl number distributions across a hypersonic turbulent boundary layer have been determined from the 'time-averaged' conservation equations using experimental mean profile data obtained at several streamwise locations in a fully developed turbulent boundary layer with negligible pressure gradient. The eddy-viscosity, mixing-length and Prandtl number results show general agreement with previous incompressible and adiabatic compressible correlations. However, when the turbulent Prandtl number is defined using total enthalpy as opposed to static enthalpy no clear correlation of the results in the outer portion of the boundary layer could be obtained.
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 10; Nov. 197
    Format: text
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  • 9
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    Control of forebody three-dimensional flow separations (1979)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The development of the turbulent symmetric and asymmetric vortex flow about the lee side of a 5 deg semiangle conical forebody at high relative incidence was investigated. The cone was immersed in a Mach 0.6 airstream at a Reynolds number of 13.5 x 10 to the 6th power based on the 1.4 m axial length of the cone. Small amounts of air injected normally or tangentially to the cone surface, but on one side of the leeward meridian and beneath the vortex farthest from the wall, were effective in biasing the asymmetry. With this reorientation of the forebody vortices, the amplitude of the side force could be reduced to the point where its direction was reversed. This phenomenon was obtained either by changing the blowing rate at constant incidence or by changing incidence at constant blowing rate. Normal injection appeared more effective than tangential injection. The contrarotating vortices in the penetrating jet flow were of opposite hand to the rotational directions of the forebody vortices. A distinctively organized and stable flow structure emerged with the jet vortices positioned above the forebody vortices.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Aerodyn. Characteristics of Controls; 49 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Vortex breakdown and control experiments in the Ames-Dryden water tunnel (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flow-field measurements have been made to determine the effects of core blowing on vortex breakdown and control. The results of these proof-of-concept experiments clearly demonstrate the usefulness of water tunnels as test platforms for advanced flow-field simulation and measurement.
    Keywords: AERODYNAMICS
    Type: NASA-TM-89410 , A-87030 , NAS 1.15:89410
    Format: application/pdf
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