Approximate Methods for Predicting Separation Properties of Laminar Boundary Layers

SummarySome new solutions for steady incompressible laminar boundary layer flow, obtained by Gortler, have been used to test the accuracy of two methods which are commonly used to predict separation. A modification of Stratford's criterion for separation is given in this paper and is probably the most accurate and the simplest of all methods at present in use. Modified numerical functions are also given for Thwaites's method of predicting the main characteristics of the boundary layer over the whole surface, which improve the accuracy of the method.

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A Method for the Calculation of 3D Boundary Layers on Practical Wing Configurations

Journal of Fluids Engineering ◽

10.1115/1.3240755 ◽

1981 ◽

Vol 103 (1) ◽

pp. 104-111 ◽

Cited By ~ 5

Author(s):

J. P. F. Lindhout ◽

G. Moek ◽

E. De Boer ◽

B. Van Den Berg

Keyword(s):

Boundary Layer ◽

Boundary Layers ◽

Boundary Layer Flow ◽

Eddy Viscosity ◽

Separated Flow ◽

Laminar Boundary Layers ◽

Eddy Viscosity Model ◽

Airplane Wing ◽

Turbulent Boundary Layer Flow ◽

Layer Flow

This paper gives a description of a calculation method for 3D turbulent and laminar boundary layers on nondevelopable surfaces. A simple eddy viscosity model is incorporated in the method. Special attention is given to the organization of the computations to circumvent as much as possible stepsize limitations. The method is also able to proceed the computation around separated flow regions. The method has been applied to the laminar boundary layer flow over a flat plate with attached cylinder, and to a turbulent boundary layer flow over an airplane wing.

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Approximate Methods of Solving the Laminar Boundary-Layer Equations

Aeronautical Quarterly ◽

10.1017/s0001925900002493 ◽

1962 ◽

Vol 13 (3) ◽

pp. 285-290 ◽

Cited By ~ 2

Author(s):

R. M. Terrill

Keyword(s):

Boundary Layer ◽

Circular Cylinder ◽

Skin Friction ◽

Boundary Layers ◽

Laminar Boundary Layer ◽

Numerical Solutions ◽

Approximate Methods ◽

Boundary Layer Equations ◽

Laminar Boundary Layers ◽

Remarkable Agreement

SummaryCurie and Skan have modified the approximate methods of Thwaites and Stratford to predict separation properties of laminar boundary layers for flow over an impermeable surface. The work of Curie and Skan has been extended by Curle to include the estimation of laminar skin friction for the whole flow. The purpose of the following note is to compare the approximate methods of Curie and Skan and Curle with the numerical results given by the author for flow past a circular cylinder. It is found that there is remarkable agreement between these approximate methods and the exact numerical solutions. This indicates that these methods can be used widely, both on account of their simplicity and their accuracy.

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THEORETICAL MODELISATION IN TRANSIENT CONVECTIVE HEAT TRANSFER FOR A LAMINAR BOUNDARY LAYER FLOW

International Symposium on Transient Convective Heat Transfer ◽

10.1615/ichmt.1996.transientconvheattransf.50 ◽

1996 ◽

Cited By ~ 1

Author(s):

Guillaume Polidori ◽

N. Chitou ◽

Jacques Padet

Keyword(s):

Heat Transfer ◽

Boundary Layer ◽

Convective Heat Transfer ◽

Convective Heat ◽

Laminar Boundary Layer ◽

Boundary Layer Flow ◽

Layer Flow

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Laminar boundary layers behind detonation waves

Proceedings of the Royal Society of London Series A - Mathematical and Physical Sciences ◽

10.1098/rspa.1983.0063 ◽

1983 ◽

Vol 387 (1793) ◽

pp. 331-349 ◽

Cited By ~ 3

Keyword(s):

Heat Transfer ◽

Boundary Layer ◽

Boundary Layers ◽

Flow Analysis ◽

Time Dependent ◽

Detonation Waves ◽

Planar Geometry ◽

Laminar Boundary Layers ◽

Spherical Detonation ◽

Layer Flow

New solutions are presented for non-stationary boundary layers induced by planar, cylindrical and spherical Chapman-Jouguet (C-J) detonation waves. The numerical results show that the Prandtl number ( Pr ) has a very significant influence on the boundary-layer-flow structure. A comparison with available time-dependent heat-transfer measurements in a planar geometry in a 2H 2 + O 2 mixture shows much better agreement with the present analysis than has been obtained previously by others. This lends confidence to the new results on boundary layers induced by cylindrical and spherical detonation waves. Only the spherical-flow analysis is given here in detail for brevity.

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