Steady state magnetic reconnection at high magnetic Reynolds number: A boundary layer analysis

1995 ◽  
Vol 100 (A10) ◽  
pp. 19277 ◽  
Author(s):  
Ferdinand Jamitzky ◽  
Manfred Scholer
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Steady State ◽  
Magnetic Reconnection ◽  
Magnetic Reynolds Number ◽  
Boundary Layer Analysis ◽  
Layer Analysis

Experience With Throat-Tap Nozzles for Accurate Flow Measurement

1972 ◽  
Vol 94 (2) ◽  
pp. 133-137 ◽  
Author(s):  
K. C. Cotton ◽  
J. A. Carcich ◽  
P. Schofield
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Turbulent Flow ◽  
Flow Measurement ◽  
Boundary Layer Analysis ◽  
The Past ◽  
Layer Analysis ◽  
Considerable Experience

During the past 10 years considerable experience has been gained in the use of ASME throat-tap nozzles for accurate flow measurement. Numerous precision calibrations have established turbulent flow coefficients up to a throat Reynolds number of 6.6 million. These results verify flow coefficients calculated from boundary-layer analysis.

A Physical Model of the Evaporating Meniscus

1988 ◽  
Vol 110 (1) ◽  
pp. 201-207 ◽  
Author(s):  
A. Mirzamoghadam ◽  
I. Catton
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Steady State ◽  
Temperature Distribution ◽  
Copper Plate ◽  
Integral Approach ◽  
Boundary Layer Analysis ◽  
Layer Analysis ◽  
And Performance ◽  
Meniscus Profile

Transport phenomena associated with the heating of a stationary fluid near saturation by an inclined, partially submerged copper plate were studied analytically. Under steady-state evaporation, the meniscus profile was derived using an appropriate liquid film velocity and temperature distribution in an integral approach similar to boundary layer analysis. Derivation of the meniscus profile led to predicting heat transfer and performance as a function of angle of inclination of the plate.

An airfoil theory of bifurcating laminar separation from thin obstacles

1990 ◽  
Vol 216 ◽  
pp. 255-284 ◽  
Author(s):  
C. J. Lee ◽  
H. K. Cheng
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Steady State ◽  
Steady State Solution ◽  
Equation System ◽  
Branch Points ◽  
Laminar Separation ◽  
Kutta Condition ◽  
Numerical Studies ◽  
Steady State Solutions

Global interaction of the boundary layer separating from an obstacle with resulting open/closed wakes is studied for a thin airfoil in a steady flow. Replacing the Kutta condition of the classical theory is the breakaway criterion of the laminar triple-deck interaction (Sychev 1972; Smith 1977), which, together with the assumption of a uniform wake/eddy pressure, leads to a nonlinear equation system for the breakaway location and wake shape. The solutions depend on a Reynolds numberReand an airfoil thickness ratio or incidence τ and, in the domain$Re^{\frac{1}{16}}\tau = O(1)$considered, the separation locations are found to be far removed from the classical Brillouin–Villat point for the breakaway from a smooth shape. Bifurcations of the steady-state solution are found among examples of symmetrical and asymmetrical flows, allowing open and closed wakes, as well as symmetry breaking in an otherwise symmetrical flow. Accordingly, the influence of thickness and incidence, as well as Reynolds number is critical in the vicinity of branch points and cut-off points where steady-state solutions can/must change branches/types. The study suggests a correspondence of this bifurcation feature with the lift hysteresis and other aerodynamic anomalies observed from wind-tunnel and numerical studies in subcritical and high-subcriticalReflows.

scholarly journals Boundary layer analysis and heat transfer of a nanofluid

2014 ◽  
Vol 17 (2) ◽  
pp. 401-412 ◽  
Author(s):  
M. M. MacDevette ◽  
T. G. Myers ◽  
B. Wetton
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Boundary Layer Analysis ◽  
Layer Analysis
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