Compressible Turbulent Boundary Layers
Title | Compressible Turbulent Boundary Layers PDF eBook |
Author | |
Publisher | |
Pages | 580 |
Release | 1969 |
Genre | Compressibility |
ISBN |
An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient
Title | An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient PDF eBook |
Author | David L. Brott |
Publisher | |
Pages | 104 |
Release | 1969 |
Genre | Compressibility |
ISBN |
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).
Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients
Title | Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients PDF eBook |
Author | Shimer Zane Pinckney |
Publisher | |
Pages | 68 |
Release | 1971 |
Genre | Boundary layer |
ISBN |
Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers
Title | Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers PDF eBook |
Author | David F. Gates |
Publisher | |
Pages | 124 |
Release | 1973 |
Genre | Supersonic nozzles |
ISBN |
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
The Compressible Turbulent Boundary Layer with Surface Mass Transfer
Title | The Compressible Turbulent Boundary Layer with Surface Mass Transfer PDF eBook |
Author | Fred Culick |
Publisher | |
Pages | 80 |
Release | 1960 |
Genre | Boundary layer |
ISBN |
Calculation Methods for Compressible Turbulent Boundary Layers, 1976
Title | Calculation Methods for Compressible Turbulent Boundary Layers, 1976 PDF eBook |
Author | Dennis M. Bushnell |
Publisher | |
Pages | 156 |
Release | 1977 |
Genre | Compressibility |
ISBN |
Compressible Turbulent Boundary Layers
Title | Compressible Turbulent Boundary Layers PDF eBook |
Author | Mitchel H.. Bertram |
Publisher | |
Pages | 580 |
Release | 1969 |
Genre | Compressibility |
ISBN |