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  • 1990-1994  (13)
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Keywords
Publisher
Years
Year
  • 1
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    Use of a rotated Riemann solver for the two-dimensional Euler equations (1993)
    Elsevier
    Details
    Publication Date: 1993-06-01
    Print ISSN: 0021-9991
    Electronic ISSN: 1090-2716
    Topics: Computer Science , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    A multidimensional flux function with applications to the Euler and Navier-Stokes equations (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: In the present grid-independent approximate Riemann solver for 2D and 3D flows that are governed by the Euler or Navier-Stokes equations, fluxes on grid faces are obtained by wave decomposition; the assumption of information-propagation in the velocity-difference directions leads to a more accurate resolution of shear and shock waves, when these are are oblique to the grid. The model, which yields significantly greater accuracy in both supersonic and subsonic first-order spatially accurate computations, describes the difference in states at each grid interface by the action of five waves.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics (ISSN 0021-9991); 105; 2; p. 306-323.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Grid-refinement study of hypersonic laminar flow over a 2-D ramp (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Computations were made for those test cases of Problem 3 which were designated as laminar flows, viz., test cases 3.1, 3.2, 3.4, and 3.5. These test cases corresponded to flows over a flat plate and a compression ramp at high Mach number and at high Reynolds number. The computations over the compression ramps indicate a substantial streamwise extent of separation. Based on previous experience with separated laminar flows at high Mach numbers which indicated a substantial effect with spatial grid refinement, a series of computations with different grid sizes were performed. Also, for the flat plate, comparisons of the results for two different algorithms were made.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 2 (A93-42576 17-02); p. 244-254.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Inviscid flux-splitting algorithms for real gases with non-equilibrium chemistry (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Formulations of inviscid flux splitting algorithms for chemical nonequilibrium gases are presented. A chemical system for air dissociation and recombination is described. Numerical results for one-dimensional shock tube and nozzle flows of air in chemical nonequilibrium are examined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics (ISSN 0021-9991); 90; 371-395
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Implicit flux-split schemes for the Euler equations (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 28; 973
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Splitting of inviscid fluxes for real gases (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Flux-vector and flux-difference splittings for the inviscid terms of the compressible flow equations are derived under the assumption of a general equation of state for a real gas in equilibrium. No necessary assumptions, approximations for auxiliary quantities are introduced. The formulas derived include several particular cases known for ideal gases and readily apply to curvilinear coordinates. Applications of the formulas in a TVD algorithm to one-dimensional shock-tube and nozzle problems show their quality and robustness.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics (ISSN 0021-9991); 87; 1-24
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    An investigation of passive control methods for shock-induced separation at hypersonic speeds (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effectiveness of several passive control techniques on shock-induced boundary-layer separation at hypersonic speed was investigated. Two approaches for alleviating the turbulent separation losses were examined: porous surface mass transfer and surface grooving. A total of four perforated surfaces with varying porosities were evaluated, and three groove orientations with respect to the freestream direction were studied. A comparison of the results from passive control techniques with those from an 'uncontrolled' shock impingement showed that the porous surface with the greatest porosity provided the greatest reduction in the pressure rise across the oblique shock wave. The grooved surface tested were found to be not effective; each of the grooved configurations examined increased the peak pressure value.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2725
    Format: text
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  • 8
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    A grid-independent approximate Riemann solver with applications to the Euler and Navier-Stokes equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new two-dimensional approximate Riemann solver has been developed that obtains fluxes on grid faces via wave decomposition. By utilizing information propagation in the velocity-difference directions rather than in the grid-normal directions, this flux function more appropriately interprets and hence more sharply resolves shock and shear waves when they lie oblique to the grid. The model uses five waves to describe the difference in states at a grid face. Two acoustic waves, one shear wave, and one entropy wave propagate in the direction defined by the local velocity difference vector, while the fifth wave is a shear wave that propagates at a right angle to the other four. Test cases presented include a shock reflecting off a wall, a pure shear wave, supersonic flow over an airfoil, and viscous separated airfoil flow. Results using the new model give significantly sharper shock and shear contours than a grid-aligned solver. Navier-Stokes computations over an aifoil show reduced pressure distortions in the separated region as a result of the grid-independent upwinding.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0239
    Format: text
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  • 9
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    Characteristic time-stepping or local preconditioning of the Euler equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A derivation is presented of a local preconditioning matrix for multidimensional Euler equations, that reduces the spread of the characteristic speeds to the lowest attainable value. Numerical experiments with this preconditioning matrix are applied to an explicit upwind discretization of the two-dimensional Euler equations, showing that this matrix significantly increases the rate of convergence to a steady solution. It is predicted that local preconditioning will also simplify convergence-acceleration boundary procedures such as the Karni (1991) procedure for the far field and the Mazaheri and Roe (1991) procedure for a solid wall.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-1552 , AIAA Computational Fluid Dynamics Conference; Jun 24, 1991 - Jun 27, 1991; Honolulu, HI; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of a multi-dimensional flux function on the monotonicity of Euler and Navier-Stokes computations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A limiting method has been devised for a grid-independent flux function for use with the two-dimensional Euler and Navier-Stokes equations. This limiting is derived from a monotonicity analysis of the model and allows for solutions with reduced oscillatory behavior while still maintaining sharper resolution than a grid-aligned method. In addition to capturing oblique waves sharply, the grid-independent flux function also reduces the entropy generated over an airfoil in an Euler computation and reduces pressure distortions in the separated boundary layer of a viscous-flow airfoil computation. The model has also been extended to three dimensions, although no angle-limiting procedure for improving monotonicity characteristics has been incorporated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1530 , AIAA Computational Fluid Dynamics Conference; Jun 24, 1991 - Jun 27, 1991; Honolulu, HI; United States
    Format: text
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