The Numerical Calculation Of Laminar Boundary Layer Separation PDF Download
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| Author | : John M. Klineberg |
| Publisher | : |
| Total Pages | : 108 |
| Release | : 1974 |
| Genre | : Boundary layer |
| ISBN | : |
Download The Numerical Calculation of Laminar Boundary-layer Separation Book in PDF, ePub and Kindle
Iterative finite-difference techniques are developed for integrating the boundary-layer equations, without approximation, through a region of reversed flow. The numerical procedures are used to calculate incompressible laminar separated flows and to investigate the conditions for regular behavior at the point of separation. Regular flows are shown to be characterized by an integrable saddle-type singularity that makes it difficult to obtain numerical solutions which pass continuously into the separated region. The singularity is removed and continuous solutions ensured by specifying the wall shear distribution and computing the pressure gradient as part of the solution. Calculated results are presented for several separated flows and the accuracy of the method is verified. A computer program listing and complete solution case are included.
| Author | : James Edward Carter |
| Publisher | : |
| Total Pages | : 72 |
| Release | : 1975 |
| Genre | : Boundary layer |
| ISBN | : |
Download Inverse Solutions for Laminar Boundary-layer Flows with Separation and Reattachment Book in PDF, ePub and Kindle
Numerical solutions of the laminar, incompressible boundary-layer equations are presented for flows involving separation and reattachment. Regular solutions are obtained with an inverse approach in which either the displacement thickness or the skin friction is specified; the pressure is deduced from the solution. A vorticity--stream-function formulation of the boundary-layer equations is used to eliminate the unknown pressure. Solutions of the resulting finite-difference equations, in which the flow direction is taken into account, are obtained by several global iteration schemes which are stable and have unconditional diagonal dominance. Results are compared with Klineberg and Steger's separated boundary-layer calculations, and with Briley's solution of the Navier-Stokes equations for a separated region. In addition, an approximate technique is presented in which the streamwise convection of vorticity is set equal to zero in the reversed flow region; such a technique results in a quick forward-marching procedure for separated flows.
| Author | : Tzuyin Wu |
| Publisher | : |
| Total Pages | : 504 |
| Release | : 1991 |
| Genre | : |
| ISBN | : |
Download Numerical Studies of Unsteady Laminar Boundary-layer Separation Over Impulsively-started Moving Objects Book in PDF, ePub and Kindle
| Author | : Laura Lynn Pauley |
| Publisher | : |
| Total Pages | : 222 |
| Release | : 1988 |
| Genre | : Laminar boundary layer |
| ISBN | : |
Download A Numerical Study of Unsteady Laminar Boundary Layer Separation Book in PDF, ePub and Kindle
The unsteady, incompressible Navier-Stokes equations were solved using a fractional timestep method. Using this technique, the separation of a laminar boundary layer under the influence of an external adverse pressure gradient was.
| Author | : Tuncer Cebeci |
| Publisher | : |
| Total Pages | : 22 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
Download Calculation of Boundary Layers Near the Stagnation Point of an Oscillating Airfoil Book in PDF, ePub and Kindle
The results of an investigation of boundary layers close to the stagnation point of an oscillating airfoil are reported. Two procedures for generating initial conditions - the characteristics-box scheme and a quasi-static approach - were investigated, and the quasi-static approach was shown to be appropriate provided the initial region was far from any flow separation. With initial conditions generated in this way, the unsteady boundary-layer equations were solved for the flow in the leading-edge region of a NACA 0012 airfoil oscillating from 0 degrees to 5 degrees. Results were obtained for both laminar and turbulent flow, and, in the latter case, the effect of transition was assessed by specifying its occurrence at different locations. The results demonstrate the validity of the numerical scheme and suggest that the procedures should be applied to calculation of the entire flow around oscillating airfoils. (Author).
| Author | : S. M. Belotserkovsky |
| Publisher | : CRC Press |
| Total Pages | : 322 |
| Release | : 1992-11-30 |
| Genre | : Technology & Engineering |
| ISBN | : 9780849393068 |
Download Two-Dimensional Separated Flows Book in PDF, ePub and Kindle
Two-Dimensional Separated Flows provides a systematic presentation of the theory of separated flow around bodies. The main classes of aerodynamic problems of plane-parallel flow around bodies are described, and the steady aerodynamic, unsteady aerodynamic, and statistical characteristics of a trailing wake are determined. Numerical methods based on the synthesis of models for non-viscous incompressible flow and boundary layer, algorithms, examples, and systematic comparisons are presented. The book also includes numerical results for the problem of separated flow around fixed, oscillating, and rotating cylinders, in addition to results for separated flow around an aerofoil over a wide range of angles. Two-Dimensional Separated Flows will benefit researchers and students studying aerodynamics, aircraft dynamics, aeroelasticity, and the aerodynamics of building structures.
| Author | : Hermann Schlichting |
| Publisher | : |
| Total Pages | : 180 |
| Release | : 1949 |
| Genre | : Boundary layer |
| ISBN | : |
Download Lecture Series "Boundary Layer Theory.": Laminar flows Book in PDF, ePub and Kindle
| Author | : K. Schröder |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1952 |
| Genre | : Aerodynamics |
| ISBN | : |
Download A Simple Numerical Method for the Calculation of the Laminar Boundary Layer Book in PDF, ePub and Kindle
An iteration difference method for the calculation of the incompressible laminar boundary layer is described. The method uses Prandtl's boundary layer equation and the boundary conditions directly and permits the attainment of an arbitrary accuracy. The method has been tested successfully in the continuation of the Blasius profile on the flat plate, on the circular cylinder investigated by Heimenz and on an elliptical cylinder of fineness ratio 1:4. The method makes possible the testing of previously developed methods, all of which contain important assumptions.
| Author | : Henry Görtler |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1954 |
| Genre | : Boundary layer |
| ISBN | : |
Download On the Three-dimensional Instability of Laminar Boundary Layers on Concave Walls Book in PDF, ePub and Kindle
A study is made of the stability of laminar boundary-layer profiles on slightly curved walls relative to small disturbances that result from vortices whose axes are parallel to the principal direction of flow. The result is an eigenvalue problem by which, for a given undisturbed flow at a prescribed wall, the amplification or decay is computed for each Reynolds number and each vortex thickness. For neutral disturbances (zero amplification) a critical Reynolds number is determined for each vortex distribution. The numerical calculation produces amplified disturbances on concave walls only.
| Author | : Morris Morduchow |
| Publisher | : |
| Total Pages | : 43 |
| Release | : 1952 |
| Genre | : Laminar boundary layer |
| ISBN | : |
Download Method for Calculation of Compressible Laminar Boundary-layer Characteristics in Axial Pressure Gradient with Zero Heat Transfer Book in PDF, ePub and Kindle
The Karman-Pohlhausen method is extended primarily to sixth-degree velocity profiles for determining the characteristics of the compressible laminar boundary layer over an adiabatic wall in the presence of an axial pressure gradient. It is assumed that the Prandtl number is unity and that the coefficient of viscosity varies linearly with the temperature. A general approximate solution which permits a rapid determination of the boundary layer characteristics for any given free-stream Mach number and given velocity distribution at the outer edge of the boundary layer is obtained. Numerical examples indicated that this solution will practice lead to results of satisfactory accuracy, including the critical Reynolds number for stability. For the special purpose of calculating the location of the separation point in an adverse pressure gradient, a short and simple method, based on the use of a seventh-degree velocity profile, is derived. The numerical example given here indicates that this method should in practice lead to sufficiently accurate results. For the special case of flow near a forward stagnation point it is shown that the Karman-Pohlhausen method with the usual fourth-degree profiles leads to results of adequate accuracy, even for the critical Reynolds number.
