3 edition of **A three-dimensional, compressible laminar boundary-layer method for general fuselages.** found in the catalog.

A three-dimensional, compressible laminar boundary-layer method for general fuselages.

- 389 Want to read
- 15 Currently reading

Published
**1990**
by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va
.

Written in English

- Boundary layer.,
- Laminar flow.

**Edition Notes**

Other titles | Three dimensional, compressible laminar boundary layer method for general fuselages. |

Statement | Yong-Sun Wie. |

Series | NASA contractor report -- 4292, vol.II., NASA contractor report -- NASA CR-4292. |

Contributions | United States. National Aeronautics and Space Administration. Scientific and Technical Information Division. |

The Physical Object | |
---|---|

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL15363899M |

methods for boundary-layer type problems that appear in the current literature can generally be categorized as (1) integral methods, (2) finite-difference/fi- nite-volume methods, or (3) finite-element methods. Integral methods can be applied to a wide range of both laminar and. This text is the translation and revision of Schlichting's classic text in boundary layer theory. The main areas covered are laws of motion for a viscous fluid, laminar boundary layers, transition and turbulence, and turbulent boundary layers.

A turbulent boundary layer is very unsteady and the streamlines do not remain parallel. The boundary layer shape represents an average of the velocity at any height. There is a region between the laminar and turbulent section where transition takes place The turbulent boundary layer exists on top of a thin laminar layer called the LAMINAR SUB File Size: KB. General solution of the laminar compressible boundary layer in the stagnation region of blunt bodies in axisymmetric flow / (Washington, D.C.: National Aeronautics and Space Administration, ), by Fred W. Matting, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust).

Audio Books & Poetry Community Audio Computers, Technology and Science Music, Arts & Culture News & Public Affairs Non-English Audio Spirituality & Religion. Librivox Free Audiobook. Academy Pod Stars Applesauce Scandalous Beauty Full text of "The Laminar Boundary Layer Equations". Small vanes installed on the upper surface of an airfoil to disturb the laminar boundary layer and induce a turbulent boundary layer. Slots These operate by allowing the high static pressure air beneath the wing to be accelerated through a nozzle and injected into the boundary layer on the upper surface of the airfoil.

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Oped to calculate three-dimensional, compressible, laminar boundary-layers for perfect gas flow on general fuselage shapes. These programs include the 3-D boundary-layer pro- gram (3DBLC), the body-oriented coordinate program (BCC), and the streamline coor.

A procedure for calculating three-dimensional, compressible laminar boundary-layer flow on general fuselage shapes is described.

The boundary-layer solutions can be obtained in either nonorthogonal body-oriented coordinates or orthogonal streamline Size: 3MB. A procedure for calculating 3-D, compressible laminar boundary layer flow on general fuselage shapes is described. The boundary layer solutions can be obtained in either nonorthogonal 'body oriented' coordinates or orthogonal streamline : Yong-Sun Wie.

A three-dimensional, compressible, laminar boundary-layer method for general fuselages. This user's manual contains a complete description of the computer programs developed to calculate three-dimensional, compressible, laminar boundary layers for perfect gas flow on general fuselage shapes.

These programs include the 3-D boundary layer Author: Yong-Sun Wie. The subjects cover laminar, transitional and turbulent boundary layers for two- and three-dimensional incompressible and compressible flows.

The viscous-inviscid coupling between the boundary layer and the inviscid flow is also addressed. The book has a large number of homework problems.

Stewartson has added yet another book to the burgeoning literature on this subject and the second in the series of Oxford Mathematical Monographs to deal with laminar boundary layers. The main aim of the book is to present an account of analytical and numerical methods in laminar compressible boundary-layer theory.

Real gas compressible laminar boundary-layer method for general fuselages. book suchAuthor: Julian D. Cole. Harris J.E., Morris D.J. () Solution of the three-dimensional compressible, laminar, and turbulent boundary-layer equations with comparisons to experimental data.

In: Richtmyer R.D. (eds) Proceedings of the Fourth International Conference on Numerical Methods in Fluid by: Ninth International Conference on Numerical Methods in Fluid Dynamics.

Editors: Soubbaramayer, Boujot, J. (Eds.) Free Preview. Buy this book eB68 € price for Spain (gross) The eBook version of this title will be available soon; ISBN ; Digitally watermarked, DRM-free; Included format: ebooks can be used on all.

Three-dimensional spatially growing perturbations in a two-dimensional compressible boundary layer are considered within the scope of linearized Navier–Stokes equations. The Cauchy problem is solved under the assumption of a finite growth rate of the by: This chapter describes a unified theory of the three-dimensional boundary layer.

The differential equation for the laminar compressible boundary layer in a “geodesic” coordinate system, which is suitable for all problems, is reviewed in the chapter.

The chapter deals with problems of rotating disks and by: Get this from a library. A three-dimensional, compressible laminar boundary-layer method for general fuselages.

Volume I, Numerical method. [Yong-Sun Wie; United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.].

Get this from a library. A three-dimensional, compressible laminar boundary-layer method for general fuselages. Volume II, User's manual. [Yong-Sun Wie; United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.]. A compressible vortex method with application to the interaction of an oblique shock wave with a boundary layer Applied Numerical Mathematics, Vol.

8, No. 3 Computation of Navier-Stokes equations for three-dimensional flow separationCited by: Extension of e N method to general three-dimensional boundary layers.

22 April | Applied Mathematics and Mechanics, Vol. 38, No. 7 The Problems of a Theoretical Description of the Transition Zone of a Laminar Boundary Layer into a Turbulent One.

Stability of compressible three-dimensional boundary-layer by: This book is an introduction to computational fluid dynamics with emphasis on the modeling and calculation of boundary-layer flows.

The subjects coverd include laminar, transitional and turbulent boundary layers for two- and three-dimensional incompressible flows. Two-dimensional Laminar Compressible Boundary- layer Programme for a Perfect Gas By C.

Sells Reports and Memoranda No. * August, Summary. A computer programme has been written to solve the steady laminar two-dimensional boundary- layer equations for a perfect gas at given wall temperature, without wall suction. The programme solvesFile Size: 2MB. A boundary-layer transition study on a sharp, 5° half-angle cone at various angles of attack was conducted at Mach Transition data were obtained with and without significantly reduced freestream acoustic disturbance levels.

A progressive downstream and upstream motion of the transition front on the windward and leeward rays, respectively, of the cone with angle of attack was observed Cited by: A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.

Fig. 1 shows the computational domain studied: it is rectangular in shape, of length L x and height L z, and the air flows from left to leading edge of the flat plate is not simulated, instead a solution to the compressible boundary layer equations at the corresponding Ma ∞ is imposed at the leftmost edge of the computational domain, i.e.

the by: 1. The 3D laminar boundary layer on a conical surface in the orthogonal coordinate system xy φ (Figure 3) is described by following self-similar equations and bound- ary conditions [10, 22]. Laminar boundary layers can be loosely classified according to their structure and the circumstances under which they are created.

The thin shear layer which develops on an oscillating body is an example of a Stokes boundary layer, while the Blasius boundary layer refers to the well-known similarity solution near an attached flat plate held in an oncoming unidirectional flow and Falkner–Skan.This book provides basic principles and theoretical foundations regarding three-dimensional attached viscous flow.

Emphasis is put on general three-dimensional attached viscous flows and not on three-dimensional boundary layers. This wider scope is necessary in view of the theoretical and practical problems to be mastered in practice.

In this post I go over the numerical solution to the compressible boundary layer equations. This is very useful when a quick estimate of shear stress, wall heat flux, or boundary layer height if necessary.

The sections of this post are: Introduction Compressibility transformation Using the general parabolic form Numerical solution using Crank-Nicolson Results and comparison.