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:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Author: James N. Moss
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 8
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Author: James N. Moss
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: James N. Moss
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721288014
Category :
Languages : en
Pages : 36
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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: Thomas D. Magruder
Publisher:
ISBN:
Category :
Languages : en
Pages : 354
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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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: Ioannis Nompelis
Publisher:
ISBN:
Category :
Languages : en
Pages : 324
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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