Author: Henk Altmann
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages :
Book Description
An Experimental Investigation of the Turbulent Boundary Layer in Supersonic Airflow
Author: Henk Altmann
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages :
Book Description
Experimental Investigation of a Turbulent Boundary Layer on a Greatly Elongated Body of Revolution in a Supersonic Flow
An experimental investigation of the turbulent boundary layer behind a forward facing step in supersonic flow
Author: Dave Robert Moore
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 106
Book Description
The report presents the results of an experimental study of the effect of a disturbance, produced by a forward facing step, on the turbulent boundary layer in compressible flow. Boundary layer total pressure surveys and direct skin friction measurements were made at six stations on each of two test surfaces. One surface was smooth and the other surface had an 0.080-inch forward facing step. The test stations were all located downstream of the step, the height of which was approximately one-half the smooth surface boundary layer thickness. Data were obtained at Mach Numbers of 2.0, 2.5, 3.0, and 3.5 and the test Reynolds Numbers, based on momentum thickness, ranged from 8,000 to 10,000 approximately. The results of this investigation indicate that the effect of the disturbance, produced by the step on the 'law of the wall' and 'velocity defect law' profiles appears to be negligible from a point approximately 10 flat plate boundary layer thicknesses downstream from the step. (Author).
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 106
Book Description
The report presents the results of an experimental study of the effect of a disturbance, produced by a forward facing step, on the turbulent boundary layer in compressible flow. Boundary layer total pressure surveys and direct skin friction measurements were made at six stations on each of two test surfaces. One surface was smooth and the other surface had an 0.080-inch forward facing step. The test stations were all located downstream of the step, the height of which was approximately one-half the smooth surface boundary layer thickness. Data were obtained at Mach Numbers of 2.0, 2.5, 3.0, and 3.5 and the test Reynolds Numbers, based on momentum thickness, ranged from 8,000 to 10,000 approximately. The results of this investigation indicate that the effect of the disturbance, produced by the step on the 'law of the wall' and 'velocity defect law' profiles appears to be negligible from a point approximately 10 flat plate boundary layer thicknesses downstream from the step. (Author).
An Experimental Investigation of a Three-dimensional Shock Wave-turbulent Boundary Layer Interaction in Supersonic Flow
Author: John Warren Welch
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 348
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 348
Book Description
Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient
Author: Chad S. Hale
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
Book Description
An Experimental Investigation of Supersonic Turbulent Boundary Layers After an Expansion Via Wall Pressure Measurements
Author: Jonathan Adam Dawson
Publisher:
ISBN:
Category :
Languages : en
Pages : 416
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 416
Book Description
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:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
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).
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
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
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 382
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 382
Book Description