Multigrid Calculation of Supersonic Potential Flow Past Inclined Elliptic Cones PDF Download

Author: Minwoo Park
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 358

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704

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Author: Martin Alden Weeks
Publisher:
ISBN:
Category :
Languages : en
Pages : 300

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Author: Mohamed M Hafez
Publisher: World Scientific
ISBN: 9814479160
Category : Science
Languages : en
Pages : 466

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The series of volumes to which this book belongs honors contributors who have made a major impact in computational fluid dynamics. This fourth volume in the series is dedicated to David Caughey on the occasion of his 60th birthday. The first volume was published in 1994 and was dedicated to Prof Antony Jameson. The second, dedicated to Earl Murman, was published in 1998. The third volume was dedicated to Robert MacCormack in 2002.Written by leading researchers from academia, government laboratories, and industry, the contributions in this volume present descriptions of the latest developments in techniques for numerical analysis of fluid flow problems, as well as applications to important problems in industry.

Author: Vincent Robert Mascitti
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52

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Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones having horizontal and vertical planes of symmetry. The geometry of the cone cross sections and surface velocities are expanded in Fourier series. The symmetry condition permits the uncoupling of lifting and nonlifting solutions. The present method reduces to Ward's theory for flow over a cone of elliptic cross section. Results are also presented for other shapes. Results by this method diverge for cross-sectional shapes where the maximum thickness is large compared with the minimum thickness. However, even for these slender-body shapes, lower order solutions are good approximations to the complete solution.

Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 654

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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723457937
Category :
Languages : en
Pages : 108

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The proper use of a computational fluid dynamics code requires a good understanding of the particular code being applied. In this report the application of CFL3D, a thin-layer Navier-Stokes code, is compared with the results obtained from PARC3D, a full Navier-Stokes code. In order to gain an understanding of the use of this code, a simple problem was chosen in which several key features of the code could be exercised. The problem chosen is a cone in supersonic flow at an angle of attack. The issues of grid resolution, grid blocking, and multigridding with CFL3D are explored. The use of multigridding resulted in a significant reduction in the computational time required to solve the problem. Solutions obtained are compared with the results using the full Navier-Stokes equations solver PARC3D. The results obtained with the CFL3D code compared well with the PARC3D solutions. Smith, Crawford F. and Podleski, Steve D. Unspecified Center COMPUTATIONAL FLUID DYNAMICS; COMPUTATIONAL GRIDS; CONICAL FLOW; MULTIGRID METHODS; NAVIER-STOKES EQUATION; SUPERSONIC FLOW; TURBULENT FLOW; ANGLE OF ATTACK; BOUNDARY LAYERS; CONICAL BODIES; FOREBODIES; PROGRAM VERIFICATION (COMPUTERS); STATIC PRESSURE...

Author: Aleksandr Ivanovich Shvet︠s︡
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 15

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An experimental investigation of three-dimensional transonic and supersonic flows past elliptic cones in an aerodynamic wind tunnel is presented. Six models of elliptic cones with different eccentricities and half-cone angles were investigated. The results are presented in graphs and compared with available theoretical and experimental data obtained by many authors. The comparisons show that the nonlinear thinbody theory agrees satisfactorily with experimental data for slender elliptic cones in a limited range of M; however, the theoretical values lie substantially lower than the experimental values, in proportion to the increases in flow velocity and cone width. Various methods used for calculating supersonic and hypersonic flows around conic bodies are reviewed, analyzed, and at times compared. Comparisons of methods such as tangential and equivalent-cone with the improved equivalent-cone method of Willi F. Jacobs show that the results of the first two agree satisfactorily with experiment only for bodies which do not deviate substantially from circular cones, though those obtained by the third method agree much better with experimental data. Optical investigations of all models at low M numbers showed that the shock fronts retain the same form of nearly circular cones and the local angle of the compression shock depends more on surface distribution along the body axis than on the shape of the body cross section. As the flow velocity increases, the shape of the shock wave in the section normal to the direction of flow approaches the shape of the body and the compression shock takes a conic, nonaxisymmetric form. (Author).

Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 984

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Author: Anthony Martellucci
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 102

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