Closure to “Discussions of ‘The Momentum Integral Approximation for Compressible Magnetogasdynamic Boundary-Layer Flow’” (1964, ASME J. Appl. Mech., 31, pp. 358–359)

1964 ◽  
Vol 31 (2) ◽  
pp. 359-359
Author(s):  
J. J. Kauzlarich ◽  
A. B. Cambel
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Flow ◽  
Integral Approximation ◽  
Layer Flow ◽  
Momentum Integral

Turbulent Boundary Layer Flow on the End Wall of a Cylindrical Vortex Chamber

1975 ◽  
Vol 189 (1) ◽  
pp. 305-315 ◽  
Author(s):  
T. J. Kotas
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Boundary Layers ◽  
Boundary Layer Flow ◽  
Three Dimensional ◽  
Vortex Chamber ◽  
Cylindrical Vortex ◽  
Layer Flow ◽  
Momentum Integral ◽  
End Wall

A presentation of some measurements of velocities in the turbulent boundary layer on the end wall of a vortex chamber. These show that the boundary layer flow is three-dimensional with large inward radial velocities. Consequently, most of the fluid entering the vortex chamber passes into the central region through the boundary layers on the end walls rather than the main space of the vortex chamber. A momentum integral solution is used to obtain an estimate of the radial flow through the end-wall boundary layers. A comparison of the theoretical curves with the experimental results gives support to the main assumptions used in the solutions.

The Calculation of Three-Dimensional Turbulent Boundary Layers: Part II: Attachment-Line Flow on an Infinite Swept Wing

1967 ◽  
Vol 18 (2) ◽  
pp. 150-164 ◽  
Author(s):  
N. A. Cumpsty ◽  
M. R. Head
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Boundary Layer Flow ◽  
Three Dimensional ◽  
Cross Flow ◽  
Swept Wing ◽  
Turbulent Boundary Layer Flow ◽  
Layer Flow ◽  
Momentum Integral ◽  
Attachment Line

SummaryAn earlier paper described a method of calculating the turbulent boundary layer flow over the rear of an infinite swept wing. It made use of an entrainment equation and momentum integral equations in streamwise and cross-flow directions, together with several auxiliary assumptions. Here the method is adapted to the calculation of the turbulent boundary layer flow along the attachment line of an infinite swept wing. In this case the cross-flow momentum integral equation reduces to the identity 0 = 0 and must be replaced by its differentiated form. Two alternative approaches are also adopted and give very similar results, in good agreement with the limited experimental data available. It is found that results can be expressed as functions of a single parameter C*, which is evidently the criterion of similarity for attachment-line flows.

The Momentum Integral Approximation for Compressible Magnetogasdynamic Boundary-Layer Flow

1963 ◽  
Vol 30 (2) ◽  
pp. 269-274 ◽  
Author(s):  
J. J. Kauzlarich ◽  
A. B. Cambel
Keyword(s):  
Magnetic Field ◽  
Boundary Layer ◽  
Magnetic Reynolds Number ◽  
Viscous Drag ◽  
Adiabatic Wall ◽  
Integral Approximation ◽  
Two Dimensional Flow ◽  
Layer Flow ◽  
Momentum Integral ◽  
The Magnetic Field

The drag of an adiabatic flat plate in an ionized gas for a constant magnetic field applied to the boundary layer on the plate is found by a momentum integral approximation of von Karman. Laminar, two-dimensional flow, zero pressure gradient, small magnetic Reynolds number, and negligible electrical conductivity outside the boundary layer are assumed. The solution is valid in particular to a continuous, perfect-gas plasma, of unitary Prandtl number, and for conditions when the interaction parameter is very small. The solution shows the following effects: The adiabatic wall temperature is independent of the magnetic field; there is an increase in the boundary-layer thickness as the magnetic-field strength is increased; and the viscous drag coefficient decreases whereas the coefficient of total drag increases.

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