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  • 1
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    Mass loss shape change and real-gas aerodynamic effects on a jovian atmospheric probe (1977)
    Elsevier
    Details
    Publication Date: 1977-05-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Direct simulation Monte Carlo and Navier-Stokes simulations of blunt body wake flows (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Numerical results obtained with direct simulation Monte Carlo and Navier-Stokes methods are presented for a Mach-20 nitrogen flow about a 70-deg blunted cone. The flow conditions simuulated are those that can be obtained in existing low-density hypersonic wind tunnels. Three sets of flow conditions are considered with freestream Knudsen numbers ranging from 0.03 to 0.001. The focus is on the wake structure: how the wake structure changes as a function of rarefaction, what the afterbody levels of heating are, and to what limits the continuum models are realistic as rarefaction in the wake is progressively increased. Calculations are made with and without an afterbody sting. Results for the after body sting are emphasizes in anticipation of an experimental study for the current flow conditions and model configuration. The Navier-Stokes calculations were made with and without slip boundary conditions. Comparisons of the results obtained with the two simulation methodologies are made for both flowfield structure and surface quantities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 32; 7; p. 1399-1406
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Direct simulation Monte Carlo and Navier-Stokes simulations of blunt body wake flows (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Numerical results obtained with direct simulation Monte Carlo and Navier-Stokes methods are presented for a Mach-20 nitrogen flow about a 70-deg blunted cone. The flow conditions simulated are those that can be obtained in existing low-density hypersonic wind tunnels. Three sets of flow conditions are considered with freestream Knudsen numbers ranging from 0.03 to 0.001. The focus is on the wake structure: how the wake structure changes as a function of rare faction, what the afterbody levels of heating are, and to what limits the continuum models are realistic as rarefunction in the wake is progressively increased. Calculations are made with and without an afterbody sting. Results for the afterbody sting are emphasized in anticipation of an experimental study for the current flow conditions and model configuration. The Navier-Stokes calculations were made with and without slip boundary conditions. Comparisons of the results obtained with the two simulation methodologies are made for both flowfield structure and surface quantities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 32; 7; p. 1399-1406
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Rarefied Flow (1998)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: Rarefaction effects are important for hypersonic applications for a wide spectrum of conditions ranging from low-density (high altitude) situations to relatively high-density flows where the characteristic dimension is small. The present chapter concentrates on two hypersonic flow problems at flow conditions that produce a significant range of rarefaction effects: corner flow with jet interaction and blunt body flow with special emphasis on the near wake, These problems were chosen because they involve complex flow interactions that have significant implications for both spacecraft and re-entry vehicles. In an effort to clarify issues associated with these two general flow problems and to enhance their respective databases, both experimental and computational contributions were executed by an international group of researchers. In some cases, multiple data sources for both experimental and computational contributions are achieved.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: Hypersonic Experimental and Computational Capability, Improvement and Validation; Volume 2; AGARD-AR-319-Vol-2
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Advances in Computational Capabilities for Hypersonic Flows (1997)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The paper reviews the growth and advances in computational capabilities for hypersonic applications over the period from the mid-1980's to the present day. The current status of the code development issues such as surface and field grid generation, algorithms, physical and chemical modeling, and validation is provided. A brief description of some of the major codes being used at NASA Langley Research Center for hypersonic continuum and rarefied flows is provided, along with their capabilities and deficiencies. A number of application examples are presented, and future areas of research to enhance accuracy, reliability, efficiency, and robustness of computational codes are discussed.
    Keywords: Aerodynamics
    Type: Future Aerospace Technology in the Service of the Alliance; Volume 3; AGARD-CP-600-Vol-3
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Rarefied Flows of Planetary Entry Capsules (1997)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The impact of rarefaction on entry capsules and spacecraft aerothermodynamics is emphasized for various aeroassist missions. The capability of the direct simulation Monte Carlo (DSMC) method to simulate such flows is demonstrated through examples of validation studies and applications. Several space flight projects and ground-based experiments are reviewed for which rarefaction effects have significant effect on spacecraft performance or experimental measurements. This review clearly demonstrates the significant role that the DSMC method plays in characterizing such flows.
    Keywords: Aerodynamics
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Hypersonic rarefied flow about a delta wing - direct simulation and comparison with experiment (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 8, Au; 2017-202
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Viscous shock-layer solutions with coupled radiation and ablation for earth entry (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 173-181
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Hypersonic rarefied flow about plates at incidence (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 1250-125
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Three-dimensional rarefied flow simulations for the Aeroassist Flight Experiment vehicle (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Hypersonic rarefied flow about the Aeroassist Flight Experiment vehicle has been investigated using a three-dimensional direct simulation Monte Carlo method. Calculations are performed for the transitional flows encountered during the vehicle's atmospheric entry for altitudes of 110 and 100 km with an entry velocity of 9.9 km/s. The simulations are performed using a five-species reacting gas model that account for rotational and vibrational internal energies. The solutions indicate that dissociation is important at altitudes of 110 km and below. Results are presented for surface pressures, convective heating, flowfield structure, and aerodynamic coefficient variations with altitude.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 52-57
    Format: text
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    NASA TECHNICAL REPORTS
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