Approximate Methods for Solving the Boundary–Layer Equations for Steady Plane Flows

2016 ◽  
pp. 195-208
Author(s):  
Hermann Schlichting ◽  
Klaus Gersten
Keyword(s):  
Boundary Layer ◽  
Approximate Methods ◽  
Boundary Layer Equations ◽  
Steady Plane

Approximate Methods of Solving the Laminar Boundary-Layer Equations

1962 ◽  
Vol 13 (3) ◽  
pp. 285-290 ◽  
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.

Numerical studies of the laminar boundary layer for Mach numbers up to 15

1969 ◽  
Vol 36 (2) ◽  
pp. 347-366 ◽  
Author(s):  
Henry A. Fitzhugh
Keyword(s):  
Boundary Layer ◽  
Skin Friction Coefficient ◽  
Order Effects ◽  
Approximate Methods ◽  
First Order ◽  
Boundary Layer Equations ◽  
Numerical Studies ◽  
Thickness Skin ◽  
Displacement Thickness ◽  
Exact Computer

A comprehensive set of exact solutions to the first-order boundary-layer equations has been computed using the finite difference computer programme of Sells, with and without wall cooling. The effects of Prandtl number, wall cooling and Mach number on separation point location were studied. Values of displacement thickness, skin friction coefficient and Stanton number are displayed graphically for the supersonic flow over a circular concave arc, for a subsonic cooled cylinder and for the case of a linearly retarded velocity distribution. The influence of pressure gradient on recovery factor was studied. Velocity and temperature profiles are shown for four cold wall cases. The exact computer results show the errors in many of the more approximate methods available for the case whereUe=U∞(1 -X/L). The importance of second-order effects and the applicability of a first-order solution are discussed briefly.

Numerical studies of the hypersonic strong interaction boundary-layer equations

AIAA Journal ◽  
1971 ◽  
Vol 9 (10) ◽  
pp. 2058-2060 ◽  
Author(s):  
M. J. WERLE ◽  
S. F. WORNOM
Keyword(s):  
Boundary Layer ◽  
Strong Interaction ◽  
Boundary Layer Equations ◽  
Numerical Studies
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