Comparison of a 3-D CFD-DSMC Solution Methodology With a Wind Tunnel Experiment PDF Download
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Author: Christopher Earl Glass
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 16
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Author: Christopher Earl Glass
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 16
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721517602
Category :
Languages : en
Pages : 28
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A solution method for problems that contain both continuum and rarefied flow regions is presented. The methodology is applied to flow about the 3-D Mars Sample Return Orbiter (MSRO) that has a highly compressed forebody flow, a shear layer where the flow separates from a forebody lip, and a low density wake. Because blunt body flow fields contain such disparate regions, employing a single numerical technique to solve the entire 3-D flow field is often impractical, or the technique does not apply. Direct simulation Monte Carlo (DSMC) could be employed to solve the entire flow field; however, the technique requires inordinate computational resources for continuum and near-continuum regions, and is best suited for the wake region. Computational fluid dynamics (CFD) will solve the high-density forebody flow, but continuum assumptions do not apply in the rarefied wake region. The CFD-DSMC approach presented herein may be a suitable way to obtain a higher fidelity solution. Glass, Christopher E. and Horvath, Thomas J. Langley Research Center NASA/TM-2002-211777, L-18212, NAS 1.15:211777
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721214440
Category :
Languages : en
Pages : 38
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A method to obtain coupled Computational Fluid Dynamics-Direct Simulation Monte Carlo (CFD-DSMC), 3-D flow field solutions for highly blunt bodies at low incidence is presented and applied to one concept of the Mars Sample Return Orbiter vehicle as a demonstration of the technique. CFD is used to solve the high-density blunt forebody flow defining an inflow boundary condition for a DSMC solution of the afterbody wake flow. By combining the two techniques in flow regions where most applicable, the entire mixed flow field is modeled in an appropriate manner. Glass, Christopher E. and Gnoffo, Peter A. Langley Research Center NASA/TM-2000-210322, NAS 1.15:210322, L-18012
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author: Thomas Edward Schwartzentruber
Publisher:
ISBN:
Category :
Languages : en
Pages : 480
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Author: Andrew D. Ketsdever
Publisher: American Institute of Physics
ISBN:
Category : Medical
Languages : en
Pages : 1118
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Book Description
The papers in these proceedings were peer reviewed. The RGD Symposia are highly inter-disciplinary and encompass all aspects of rarefaction and non-equilibrium phenomena in gases. Rarefied flow phenomena include the mechanics and physics of low density gases and the analysis of flows which take place on a spatial scale comparable to the mean free path of a gas. Topics covered include: Kinetic theory and transport theory; numerical methods including direct simulation Monte Carlo and molecular dynamics; gas-surface phenomena; nano- and microscale flows; molecular beams, atom and molecular optics; clusters and aerosols; external flows including space and vacuum technologies; plume flows; hypersonic flows; molecular collision dynamics; relaxation processes; ionized gas flows; physics of the space environment; plasma processing; experimental techniques; diagnostics including laser induced fluorescence and electron beams; applications. With the increase in space activities and microfabrication capabilities, new themes have emerged including rarefied hypersonic flows, non-equilibrium gases, plasma processing, nano- and micro-scale flows at relatively high pressures, along with parallel and hybrid computational developments. Because the RGD Symposia are recognized as the principle forum for the presentation of recent advances in this field, it is a must for engineers and scientists in a variety of specialties.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
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Author: Montgomery Hughson
Publisher:
ISBN: 9781423547211
Category : Aerodynamics
Languages : en
Pages : 122
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Numerical simulation of maneuvering vehicles is accomplished using a three dimensional (3-D) unstructured computational fluid dynamic (CFD) method. The equations of fluid motion used are either the inviscid Euler equations or the full viscous Navier Stokes equations cast in an Arbitrary Lagrangian- Eulerian (ALE) framework. A turbulence model developed by Spalart and Allmaras is used for viscous solutions. The system of fluid equations are solved implicitly using upwind, flux-splitting techniques for the convective fluxes of either Roe or Van Leer with up to second-order temporal and spatial accuracy for steady or unsteady computations. Innovative boundary conditions for a moving mesh to include inviscid, viscous, far-field and a solid rocket motor exhaust exit surface were developed. The temporal solution is found using an application of Newton's method. The computational field simulation (CFS) of two 3-D wings and a waisted-body of revolution are compared to experimental data for boundary condition validation. An unsteady CFS of a pitching wing is validated by comparison to experimental data. A number of unsteady missile maneuver trajectories coupled with a six degree of freedom model using Euler angles and the Flat-Earth model are presented.
Author: American Institute of Aeronautics and Astronautics. Technical Information Service
Publisher:
ISBN:
Category : AIAA paper
Languages : en
Pages : 184
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