Author: Walter G. HoydyshPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 14
Book Description
An Experimental Investigation of Hypersonic Turbulent Boundary Layers in Adverse Pressure Gradient
Author: Walter G. HoydyshPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 14
Book Description
A Theoretical and Experimental Investigation of the Hypersonic Turbulent Boundary Layer Undergoing Both Adverse Pressure Gradient and Cross Flow Along a Windward Plane of Symmetry
Author: Wladimiro CalareseExperimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient
Author: Chad S. HalePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
Book Description
An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient
Author: Walter B. SturekPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 382
Book Description
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. SturekPublisher:
ISBN:
Category :
Languages : en
Pages : 129
Book Description
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).
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. SturekPublisher:
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 and Analytical Investigation of Hypersonic Inlet Boundary Layers: Data reduction program and tabulated experimental data
Author: J. F. StroudPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 410
Book Description
Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
An Experimental Investigation of the Influence of Strong Adverse Pressure Gradients on Turbulent Boundary Layers at Supersonic Speeds
Author: Georg DrouggeAn Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers
Author: J. F. StroudPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 118
Book Description
Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
An Experimental Investigation of Turbulent Supersonic Boundary Layer Flow in an Adverse Pressure Gradient
Author: Edward GootzaitPublisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 322
Book Description