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  • 1
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    Magnetized Positive Column between Coaxial Cylinders (1986)
    Institute of Physics
    Details
    Publication Date: 1986-02-01
    Print ISSN: 0031-8949
    Electronic ISSN: 1402-4896
    Topics: Physics
    Published by Institute of Physics
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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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    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
  • 5
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    Rarefaction effects for hypersonic re-entry flow (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 26; 392
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Hypersonic rarefied flow past spheres including wake structure (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results of a numerical study using the direct simulation Monte Carlo method are presented for hypersonic rarefied flow past spheres. The flow conditions considered are those corresponding to low density wind tunnel test conditions. The set of the experimental conditions for the calculations encompasses the transitional to near-continuum flow regimes. Comparison of the calculated drag with experimental results shows good agreement to well within the experimental error. Particular attention is focused on the wake structure. Calculations show that the wake is very rarefied with considerable thermal nonequilibrium for all the cases considered. No flow separation is observed in the wake for the near-continuum case where a vortex has been predicted by Navier-Stokes type calculations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0495
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    DSMC simulations of Mach 20 nitrogen flows about a 70 degree blunted cone and its wake (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical results obtained with the direct simulation Monte Carlo (DSMC) method are presented for 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 simulated with freestream Knudsen numbers ranging from 0.03 to 0.001. The focus is to characterize the wake flow under rarefied conditions. This is accomplished by calculating the influence of rarefaction on wake structure along with the impact that an afterbody has on flow features. This data report presents extensive information concerning flowfield features and surface quantities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-107762 , NAS 1.15:107762
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Nonequilibrium thermal radiation for an aeroassist flight experiment vehicle (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The direct-simulation Monte Carlo method incorporating a dissociating and ionizing gas model for air with thermal radiation is used to characterize the hypersonic flow about an axisymmetric representation of an aeroassist flight experiment (AFE) vehicle, whose freestream conditions correspond to selected points along the entry, aerobraking, and exit phases of the trajectory. Calculations for two trajectory conditions indicate that the radiative heating of the AFE forebody is lower than the convective heating, but becomes significant as the maximum convective heating rate condition is approached.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0081
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Aerothermodynamics of a 1.6-m-diameter sphere in hypersonic rarefied flow (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for hypersonic rarefied flow about a 1.6-m-diameter sphere. The flow conditions considered are those experienced by a typical satellite in orbit or by a space vehicle during entry. The altitude range considered is that from 90 to 200 km, which encompasses the near continuum, transitional and free-molecular flow regimes. A freestream velocity of 7.5 km/s is assumed in the simulations. The results show that transitional effects are significant at all altitudes below 200 km, but at 200 km the flow about the sphere attains the free-molecular limit. Very little chemical activity is present above 120 km. Both the stagnation point heat transfer and the sphere drag approach their respective free molecule values at 200 km. Results highlight the thermal and chemical nonequilibrium nature of the flowfield. Nonequilibrium effects on the surface heating and body drag are also investigated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0773
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Hypersonic rarefied flow about plates at incidence (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The direct-simulation Monte Carlo method has been used in a numerical study of the transitional flow about two plate configurations at incidence; one of the two plates, both of which are 12 m long, has zero thickness, while the other has a thickness of 0.5 m and a node radius of 0.5 m. The flow conditions simulated are those of the Space Shuttle Orbiter during 7.5 km/hr reentry, in the 200-100 km altitude range encompassing most of the transitional flow for this vehicle. The results obtained clearly demonstrate that transitional effects are significant even at those altitudes where the flow about a typical space vehicle has been considered free-molecular.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-1712
    Format: text
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