An Integral Method for Three-dimensional, Compressible, Laminar Boundary Layers with Mass Injection PDF Download
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Author: Sang-Wook Kang
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 138
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Author: Sang-Wook Kang
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 138
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Book Description
Author: Eli Reshotko
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1368
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Author: G. S. Raetz
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 33
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Book Description
A numerical method of calculating the laminar boundary layer on any three-dimensional surface in steady compressible flow is presented. This method can be applied readily on an automatic digital computer with any desired accuracy. It is valid at and near the usual singular points and lines of a surface as well as elsewhere. A principle clarifying various aspects of three-dimensional flow also is given. (Author).
Author: Torstein K. Fannelop
Publisher:
ISBN:
Category :
Languages : en
Pages : 165
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The general three-dimensional laminar compressible boundary-layer equations, written in terms of streamline coordinates, are reduced to a sequence of two-dimensional equations by means of a systematic perturbation procedure. The perturbation parameter is related to the inviscid streamline curvature and the lowest (zeroth-order) equations are identical with the small crossflow equations of Hayes. In addition, the equations for the first-order terms are given explicitly both in terms of physical and transformed (Lees-Levy) variables. Two alternate finite difference methods (for physical and transformed variables respectively) are developed to solve the zeroth as well as the first-order equations exactly. Local similarity methods are also considered for comparison. A variety of boundary conditions are possible including the case for which the heat and mass-transfer rates are coupled through an energy balance. The methods were applied to the problem of boundary-layer flow on a blunted cone at angle-of-attack. The results show that the crossflow often becomes rather large near the wall. The first-order corrections to the enthalpy and tangential velocity in the boundary layer are nevertheless small. (Author).
Author: Bilal Hafeez Mughal
Publisher:
ISBN:
Category :
Languages : en
Pages : 148
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 720
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 668
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 620
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 912
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