Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer
Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer

Author: Robert L. P. Voisinet

Publisher:

Published: 1973

Total Pages: 144

ISBN-13:

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The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).

An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part II. Analysis of the Experimental Data
An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part II. Analysis of the Experimental Data

Author: W. B. Sturek

Publisher:

Published: 1971

Total Pages: 58

ISBN-13:

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The experimental data reported in Part 1 are analyzed. Turbulent boundary layer equations applicable to compressible flow over a surface with longitudinal curvature are evaluated by numerical integration using the tabulated profile data. Curvature corrections to the equation for conservation of streamwise momentum are shown to be small but of the same order of magnitude as the wall shear stress. The data are shown to correlate in law of the wall and velocity defect dimensionless coordinates using an integral compressibility transformation. Values of skin friction coefficient calculated using the experimental data are compared to other experimental data and to values predicted using the Spalding-Chi method. (Author).

An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part I.A Detailed Description of the Experiment and Data Tabulation
An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part I.A Detailed Description of the Experiment and Data Tabulation

Author: Walter B. Sturek

Publisher:

Published: 1970

Total Pages: 129

ISBN-13:

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Experimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of zero pressure gradient and in a region of moderate adverse pressure gradient along the curved surface of an isentropic ramp model are reported. Detailed surveys of impact pressure, static pressure and total temperature were taken through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made in a supersonic wind tunnel for a nominal tunnel nozzle setting of Mach 3.5. The data are for an adiabatic wall with values of momentum thickness Reynolds number ranging from 19,000 to 42,000. The experiment is described in detail and the mean profile data are presented in tabular form. Fluctuation data obtained using constant temperature hot wire anemometry are presented for one station in the region of zero pressure gradient and for one station in the region of adverse pressure gradient. (Author).