Hypersonic Shock Interactions about a 25 Deg/65 Deg Sharp Double Cone PDF Download
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721512232
Category :
Languages : en
Pages : 28
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Book Description
This paper presents the results of a numerical study of shock interactions resulting from Mach 10 air flow about a sharp double cone. Computations are made with the direct simulation Monte Carlo (DSMC) method by using two different codes: the G2 code of Bird and the DAC (DSMC Analysis Code) code of LeBeau. The flow conditions are the pretest nominal free-stream conditions specified for the ONERA R5Ch low-density wind tunnel. The focus is on the sensitivity of the interactions to grid resolution while providing information concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction. Moss, James N. and LeBeau, Gerald J. and Glass, Christopher E. Johnson Space Center; Langley Research Center NASA/TM-2002-211778, L-18199, NAS 1.15:211778
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721512232
Category :
Languages : en
Pages : 28
Get Book Here
Book Description
This paper presents the results of a numerical study of shock interactions resulting from Mach 10 air flow about a sharp double cone. Computations are made with the direct simulation Monte Carlo (DSMC) method by using two different codes: the G2 code of Bird and the DAC (DSMC Analysis Code) code of LeBeau. The flow conditions are the pretest nominal free-stream conditions specified for the ONERA R5Ch low-density wind tunnel. The focus is on the sensitivity of the interactions to grid resolution while providing information concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction. Moss, James N. and LeBeau, Gerald J. and Glass, Christopher E. Johnson Space Center; Langley Research Center NASA/TM-2002-211778, L-18199, NAS 1.15:211778
Author: James N. Moss
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 8
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
Author: James N. Moss
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Thomas D. Magruder
Publisher:
ISBN:
Category :
Languages : en
Pages : 354
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
This paper presents the results of a numerical study of shock interactions resulting from Mach 10 flow about sharp double cones. Computations are made by using the direct simulation Monte Carlo (DSMC) method of Bird. The sensitivity and characteristics of the interactions are examined by varying flow conditions, model size, and configuration. The range of conditions investigated includes those for which experiments have been or will be performed in the ONERA R5Ch low-density wind tunnel and the Calspan-University of Buffalo Research Center (CUBRC) Large Energy National Shock (LENS) tunnel.
Author: James N. Moss
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Book Description
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: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721288014
Category :
Languages : en
Pages : 36
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Book Description
This paper presents the results of a numerical study that examines the surface heating discrepancies observed between computed and measured values along a sharp cone. With Mach numbers of an order of 10 and the freestream length Reynolds number of an order of 10 000, the present computations have been made with the direct simulation Monte Carlo (DSMC) method by using the G2 code of Bird. The flow conditions are those specified for two experiments conducted in the Veridian 48-inch Hypersonic Shock Tunnel. Axisymmetric simulations are made since the test model was assumed to be at zero incidence. Details of the current calculations are presented, along with comparisons between the experimental data, for surface heating and pressure distributions. Results of the comparisons show major differences in measured and calculated results for heating distributions, with differences in excess of 25 percent for the two cases examined. Moss, James N. Langley Research Center NASA/TM-2001-211253, NAS 1.15:211253, L-18122
Author: James N. Moss
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 30
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Book Description
This paper describes the results of a numerical study of interacting hypersonic flows at conditions that can be produced in ground-based test facilities. The computations are made with the direct simulation Monte Carlo (DSMC) method of Bird. The focus is on Mach 10 flows about flared axisymmetric configurations, both hollow cylinder flares and double cones. The flow conditions are those for which experiments have been or will be performed in the ONERA R5Ch low-density wind tunnel and the Calspan-University of Buffalo Research Center (CUBRC) Large Energy National Shock (LENS) tunnel. The range of flow conditions, model configurations, and model sizes provides a significant range of shock/shock and shock/boundary layer interactions at low Reynolds number conditions. Results presented will highlight the sensitivity of the calculations to grid resolution, contrast the difference in flow structure for hypersonic cold flows and those of more energetic but still low enthalpy flows, and compare the present results with experimental measurements for surface heating, pressure, and extent of separation.
