Author: Robert Earl WilsonPublisher:
ISBN:
Category :
Languages : en
Pages : 110
Book Description
An Experimental Investigation of Separated Turbulent Supersonic Flow at M
Author: Robert Earl WilsonExperimental Investigation of the Pressure Rise Required for the Incipient Separation of Turbulent Boundary Layers in Two-dimensional Supersonic Flow
Author: Donald M. KuehnPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Experimental Investigation of Pressure Rise Required for Incipient Separation of Turbulent Boundary Layers in 2-dimensional Supersonic Flow [with List of References]
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Author: Experimental Investigation of Supersonic Flow Separation Over a Rearward Facing Step
Author: Jain-Ming WuPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 10
Book Description
Experimental Investigation of a Turbulent Boundary Layer on a Greatly Elongated Body of Revolution in a Supersonic Flow
Author: V. M. KovalenkoAn Experimental Investigation of Heat Transfer Effects on Boundary Layer Separation in Supersonic Flow
Author: G. E. GaddAn Experimental Investigation of Turbulent Separated Boundary Layers at Low Supersonic Mach Numbers
Author: Robert E. WilsonAn Experimental Investigation of a Three-dimensional Shock Wave-turbulent Boundary Layer Interaction in Supersonic Flow
Author: John Warren WelchPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 348
Book Description
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
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).