An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient write by David L. Brott. This book was released on 1969. An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient available in PDF, EPUB and Kindle. 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).
An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient
An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient write by David L. Brott. This book was released on 1969. An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient available in PDF, EPUB and Kindle. 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).
An Experimental Investigation of a Compressible Turbulent Boundary Layer Subjected to a Systematic Variation of Adverse Pressure Gradients
An Experimental Investigation of a Compressible Turbulent Boundary Layer Subjected to a Systematic Variation of Adverse Pressure Gradients - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of a Compressible Turbulent Boundary Layer Subjected to a Systematic Variation of Adverse Pressure Gradients write by Paul John Waltrup. This book was released on 1971. An Experimental Investigation of a Compressible Turbulent Boundary Layer Subjected to a Systematic Variation of Adverse Pressure Gradients available in PDF, EPUB and Kindle.
An Experimental Investigation of Compressible Turbulent Boundary Layers in an Adverse Pressure Gradient with and Without Surface Curvature
An Experimental Investigation of Compressible Turbulent Boundary Layers in an Adverse Pressure Gradient with and Without Surface Curvature - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook An Experimental Investigation of Compressible Turbulent Boundary Layers in an Adverse Pressure Gradient with and Without Surface Curvature write by Jung-Hua Chou. This book was released on 1982. An Experimental Investigation of Compressible Turbulent Boundary Layers in an Adverse Pressure Gradient with and Without Surface Curvature available in PDF, EPUB and Kindle.
Experimental Investigation of Compressible Boundary Layers Under the Influence of Pressure Gradients
Experimental Investigation of Compressible Boundary Layers Under the Influence of Pressure Gradients - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Experimental Investigation of Compressible Boundary Layers Under the Influence of Pressure Gradients write by Raymond C. Wier. This book was released on 1996-12-01. Experimental Investigation of Compressible Boundary Layers Under the Influence of Pressure Gradients available in PDF, EPUB and Kindle. 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.
