An Experimental Investigation of Compressible Turbulent Boundary Layers in an Adverse Pressure Gradient with and Without Surface Curvature PDF Download
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Author: Jung-Hua Chou
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 258
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Author: Jung-Hua Chou
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 258
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Author: David L. Brott
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 104
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The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author).
Author: W. B. Sturek
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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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).
Author: Shimer Zane Pinckney
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68
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Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 32
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A numerical study has been performed using a finite-difference boundary layer computer program that includes corrections to the equations of motion for longitudinal curvature and allows the static pressure to be specified as a known function of x and y. Calculations with and without the corrections for longitudinal curvature and pressure gradient normal to be the local surface have been compared to experimental measurements of a supersonic turbulent boundary layer flow over a surface with concave longitudinal curvature. Substantially improved agreement with experimental measurements is obtained for the calculations including corrections for wall curvature and pressure gradient normal to the local surface for density profile, skin friction coefficient, and boundary-layer integral properties.
Author: Raymond C. Wier
Publisher:
ISBN: 9781423574361
Category : Compressibility
Languages : en
Pages : 149
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This study examined the effect of mild pressure gradients on the mean and turbulent flow of high-speed boundary layers. Three Mach numbers (1.7, 3.0 and 5.0) were investigated. Three pressure gradients were examined; a zero pressure gradient (ZPG), a favorable pressure gradient (FPG), and a combined pressure gradient (CPG). The CPG consisted of an adverse pressure gradient followed by a favorable pressure gradient. Conventional pressure probes, hot- wire and particle image velocimetry (PIV) were used to examine the flow. Measurement included mean velocity, velocity turbulence intensity, mass flux turbulence intensity and energy spectra. Instantaneous (10 nsec) Mie scattering flow visualizations were acquired. Qualitatively, the flow visualizations indicated that the turbulent flow structures were strongly affected by the pressure gradients. For the Mach 2,8 case, the PIV contours and the hot-wire profiles both indicated that the boundary layer thickness increased by 40% and decreased by 100% relative to the ZPG for the favorable and adverse pressure gradients, respectively. Further, the PIV and hot-wire data indicated that the axial turbulence intensity levels increased by 22% for the CPG and decreased by 25% for the FPG. The energy spectra data indicated that once a pressure gradient was applied (favorable or adverse) the low frequency energy increased followed by a rapid decay. Lastly, it was found that nominally 20 to 30 PIV images were sufficient for mean flow boundary layer velocities, but 93 images (the maximum recorded in this study) were insufficient to adequately resolve Reynolds shear stresses.
Author: Ronald M. C. So
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 276
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Author: Paul John Waltrup
Publisher:
ISBN:
Category :
Languages : en
Pages : 232
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Joseph Alfred Schetz
Publisher:
ISBN:
Category :
Languages : en
Pages :
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