Numerical Investigation of Gas-particle Supersonic Flow PDF Download
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Author: Mihir A. Samel
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 78
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Author: Mihir A. Samel
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 78
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Author: V. I. Timoshenko
Publisher:
ISBN:
Category :
Languages : en
Pages : 5
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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: Morris M. Penny
Publisher:
ISBN:
Category :
Languages : en
Pages : 204
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This report describes a numerical solution for chemically reacting supersonic gas-particle flows in rocket nozzles and exhaust plumes. The gas-particle flow solution is fully coupled in that the effects of particle drag and heat transfer between the gas and particle phases is treated. Gas and particulates exchange momentum via the drag exerted on the gas by the particles. Energy is exchanged between the phases via heat transfer (convection and/or radiation between the gas-particle phases). Basic assumptions made in the development of the governing equations are similar to those employed by previous investigators. The primary exception is the treatment of chemical effects in the gas phase. Thermochemistry calculations (chemical equilibrium, frozen or chemical kinetics) are shown to be uncoupled from the flow solution and, as such, can be solved separately. The solution to the set of governing equations is obtained by utilizing the method of characteristics. The equations cast in characteristic form are shown to be formally the same for ideal, frozen, chemical equilibrium and chemical non-equilibrium reacting gas mixtures. The characteristic directions for the gas-particle system are found to be the conventional gas Mach lines, the gas streamlines and the particle streamlines.
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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: R. Elangovan
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Steven Mark Sahm
Publisher:
ISBN:
Category :
Languages : en
Pages : 254
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Author: Xuepeng Guo
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 148
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Author: Leo Patrick O'Hare
Publisher:
ISBN:
Category :
Languages : en
Pages : 206
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