A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies PDF Download
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Author: George D. Catalano
Publisher:
ISBN: 9781423550181
Category :
Languages : en
Pages : 62
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Book Description
A computational fluid dynamics (CFD) approach to predicting high- speed aerodynamic flow fields of interest to the U.S. Army Research Laboratory (ARL) has been carried out The aerodynamic problems of particular interest are: (1) supersonic flow past the aftbody of projectiles with base mass injection, (2) supersonic flow past the M549 projectile, and (3) subsonic, transonic, and supersonic flow past an M864 projectile with base bleed and wake combustion. The commercially available FLUENT (Fluent, Inc. FLUENT. Version 5.1.1, Lebanon, NH, 1999.) CFD code was utilized. The computational effort supports an ongoing ARL- sponsored experimental investigation. Of particular interest in the present investigation is the careful characterization of the various turbulence models employed in the CFD code. Additionally, the ease of use and set-up as well as the computational time will be described. An experimental effort (Dutton, J. C., and A. L. Addy. 'Fluid Dynamic Mechanisms and Interactions Within Separated Flows'. U.S. Army Research Office Research Grant DAAH04-93-G-0226 and the Department of Mechanical and Industrial Engineering, University of illinois, Urbana-Champagne, Urbana, IL, August 1998.) consisting of detailed laser Doppler velocimeter (LDV), particle image velocimeter (PIV), and high-speed wall pressure measurements has been made in axisymmetric and planar subsonic and supersonic flows with embedded separated regions. The present work seeks to predict similar flow fields computationally and to address areas of agreement and disagreement.
Author: George D. Catalano
Publisher:
ISBN: 9781423550181
Category :
Languages : en
Pages : 62
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Book Description
A computational fluid dynamics (CFD) approach to predicting high- speed aerodynamic flow fields of interest to the U.S. Army Research Laboratory (ARL) has been carried out The aerodynamic problems of particular interest are: (1) supersonic flow past the aftbody of projectiles with base mass injection, (2) supersonic flow past the M549 projectile, and (3) subsonic, transonic, and supersonic flow past an M864 projectile with base bleed and wake combustion. The commercially available FLUENT (Fluent, Inc. FLUENT. Version 5.1.1, Lebanon, NH, 1999.) CFD code was utilized. The computational effort supports an ongoing ARL- sponsored experimental investigation. Of particular interest in the present investigation is the careful characterization of the various turbulence models employed in the CFD code. Additionally, the ease of use and set-up as well as the computational time will be described. An experimental effort (Dutton, J. C., and A. L. Addy. 'Fluid Dynamic Mechanisms and Interactions Within Separated Flows'. U.S. Army Research Office Research Grant DAAH04-93-G-0226 and the Department of Mechanical and Industrial Engineering, University of illinois, Urbana-Champagne, Urbana, IL, August 1998.) consisting of detailed laser Doppler velocimeter (LDV), particle image velocimeter (PIV), and high-speed wall pressure measurements has been made in axisymmetric and planar subsonic and supersonic flows with embedded separated regions. The present work seeks to predict similar flow fields computationally and to address areas of agreement and disagreement.
Author: P. Kevin Tucker
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
A numerical investigation has been made for supersonic flow past a cylindrical aft body with and without base bleed and a cylindrical boat tail. Comparison was made to available experimental data. The effect of grid cell density and turbulence models were examined. The calculation of the base flow region was much more highly dependent on grid density that was the forebody or outer flow field Agreement between the numerical and experimental results improved with the inclusion of the base bleed.
Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
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Book Description
Some 100 numerical computations have been carried out for unyawed bodies of revolution with detached bow waves. The gas is assumed perfect with y=5/3, 7/5, or 1. Free-stream Mach numbers are taken as 1.2, 1.5, 2, 3, 4, 6, 10, and [infinity symbol]. The results are summarized with emphasis on the sphere and paraboloid.
Author: Hermann Fasel
Publisher:
ISBN:
Category :
Languages : en
Pages : 153
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Book Description
A numerical method has been developed for solving the complete compressible Navier Stokes equations. The method was used to investigate the time dependent behavior of disturbances in the laminar and turbulent near wake of axisymmetric bluff bodies and their influence on and interaction with the global flow field. The equations are solved in a cylindrical coordinate system using finite difference approximations of fourth-order accuracy in space and time. Direct Numerical Simulations (DNS) were performed for a subsonic free stream Mach number of M to infinity = 0.2 and for supersonic free stream Mach numbers of M to infinity = 1.2 and M to infinity = 2.46.
Author: Paul Kevin Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 116
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Book Description
Author: H. Sugiyama
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 9
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Book Description
An inverse method was developed for treating gas-particle supersonic flow past axisymmetric blunt bodies. This method is based on two transformations (von Mises and an additional one), which are convenient for determining the shock-layer flow fields and the body shapes. In using the present method, the pure gas flow fields around spheres were first solved numerically for the freestream Mach numbers = 10, 6, 4, 3, 2 and 1.5. These were found to be in very good agreement with the available results of Van Dyke and Gordon. Then the gas-solid-particle flow in the shock layer around blunt bodies (nearly spheres) were solved for the freestream Mach numbers = 10 and 1.5, with freesteam loading ratios = 0, 0.2, 0.5 and 1.0 and particle diameters 1, 2, 5 and 10 micrometers respectively.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Xuepeng Guo
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 148
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Book Description
