Author: Georg DrouggePublisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
An Experimental Investigation of the Influence of Strong Adverse Pressure Gradients on Turbulent Boundary Layers at Supersonic Speeds
Author: Georg DrouggeAn Experimental Investigation of the Influence of Strong Adverse Presure Gradients on Turbulent Boundary Layers at Supersonic Speeds
Author: Georg DrouggeTechnical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1038
Book Description
Technical Note
Author: Experimental 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
WADC Technical Report
Author: United States. Wright Air Development DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1246
Book Description
Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient
Author: Chad S. HalePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 280
Book Description
Experimental Investigation of the Effects of Suction on a Turbulent Supersonic Boundary Layer in an Adverse Pressure Gradient
Author: James Frederick JohnsonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 226
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
Author: Walter B. SturekPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 382
Book Description