On a boundary layer phenomenon in Mindlin-Reissner plate theory for laminated circular sector plates

2001 ◽  
Vol 151 (3-4) ◽  
pp. 149-161 ◽  
Author(s):  
A. Nosier ◽  
A. Yavari ◽  
S. Sarkani
Keyword(s):  
Boundary Layer ◽  
Plate Theory ◽  
Circular Sector ◽  
Reissner Plate

Bending of a Thin Reissner Plate With a Through Crack

1991 ◽  
Vol 58 (3) ◽  
pp. 842-846 ◽  
Author(s):  
P. F. Joseph ◽  
F. Erdogan
Keyword(s):  
Boundary Layer ◽  
Plate Theory ◽  
Plate Thickness ◽  
Asymptotic Result ◽  
Leading Order ◽  
Classical Plate Theory ◽  
Outer Solution ◽  
Reissner Plate ◽  
Perturbation Problem ◽  
Title Problem

The title problem was first considered by Knowles and Wang (1960) and was shown to be related to the solution given by the classical plate theory. This solution is actually the outer solution of a singular perturbation problem, and therefore is valid only away from the crack-tip region. Within a boundary layer of order h/a, where h is the plate thickness and a is the half-crack length, the two theories differ considerably. In this study the leading order solution is obtained for h/a - 0 and it is shown that the limiting stress intensity factor given by the Reissner plate theory is more than 50 percent higher than the asymptotic result (1 + v)/(3 + v) which is obtained from the displacement field as given by the classical plate theory.

Comparison of Inviscid Computations With Theory and Experiment in Vibrating Transonic Compressor Cascades

1990 ◽  
Author(s):  
G. A. Gerolymos ◽  
E. Blin ◽  
H. Quiniou
Keyword(s):  
Boundary Layer ◽  
Plate Theory ◽  
Strong Shock ◽  
Acoustic Resonance ◽  
Boundary Layer Separation ◽  
Computational Method ◽  
Viscous Effects ◽  
Transonic Compressor ◽  
Boundary Layer Interaction ◽  
Interaction Regions

The prediction of unsteady flow in vibrating transonic cascades is essential in assessing the aeroelastic stability of fans and compressors. In the present work an existing computational code, based on the numerical integration of the unsteady Euler equations, in blade-to-blade surface formulation, is validated by comparison with available theoretical and experimental results. Comparison with the flat plate theory of Verdon is, globally, satisfactory. Nevertheless, the computational results do not exhibit any particular behaviour at acoustic resonance. The use of a 1-D nonreflecting boundary condition does not significantly alter the results. Comparison of the computational method with experimental data from started and unstarted supersonic flows, with strong shock waves, reveals that, notwithstanding the globally satisfactory performance of the method, viscous effects are prominent at the shock wave/boundary layer interaction regions, where boundary layer separation introduces a pressure harmonic phase shift, which is not presicted by inviscid methods.

Modeling of anisotropic boundary layer effects in plate theory

PAMM ◽  
2018 ◽  
Vol 18 (1) ◽  
Author(s):  
Patrick Schneider ◽  
Reinhold Kienzler
Keyword(s):  
Boundary Layer ◽  
Plate Theory

A Simple Theory for the Two-Dimensional Compressible Turbulent Boundary Layer

1972 ◽  
Vol 94 (3) ◽  
pp. 636-642 ◽  
Author(s):  
F. M. White ◽  
G. H. Christoph
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Flat Plate ◽  
Skin Friction ◽  
Plate Theory ◽  
Momentum Equation ◽  
Shape Factors ◽  
Law Of The Wall ◽  
Compressible Turbulent Flow ◽  
New Equation

A new approach is proposed for analyzing the compressible turbulent boundary layer with arbitrary pressure gradient. Utilizing a compressible law-of-the-wall and a Crocco energy approximation, the new theory integrates the momentum equation across the boundary layer in terms of inner variables only. The result is a single first-order ordinary differential equation for skin friction, devoid of integral thicknesses and shape factors. When analyzed for flat plate flow, this new equation has an exact solution apparently superior in accuracy to any other flat plate theory (Table 1). The new equation also agrees well with supersonic skin friction data in both favorable and adverse pressure gradients. The new theory contains an explicit separation criterion and is the simplest and possibly most accurate existing analysis for compressible turbulent flow.

A sectorial element based on Reissner plate theory

2000 ◽  
Vol 9 (6) ◽  
pp. 519-540 ◽  
Author(s):  
A. Yalcin Akoz ◽  
Nihal Eratli
Keyword(s):  
Plate Theory ◽  
Reissner Plate
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