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  • 11
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    Experimental investigation of transverse-mode solid-propellant combustion instability in a vortex burner (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Transverse-mode solid-propellant combustion instability in vortex burner
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-3708
    Format: application/pdf
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  • 12
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    Study of composite solid-propellant flame structure using a spectral radiation shadowgraph technique. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-05-24
    Description: Composite solid propellant flame structure in vicinity of burning surface based on spectral radiation shadowgraph technique
    Keywords: PROPELLANTS
    Type: AIAA PAPER 65-60
    Format: text
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  • 13
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    Multigrid calculation of three-dimensional viscous cascade flows (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 3-D code for viscous cascade flow prediction was developed. The space discretization uses a cell-centered scheme with eigenvalue scaling to weigh the artificial dissipation terms. Computational efficiency of a four stage Runge-Kutta scheme is enhanced by using variable coefficients, implicit residual smoothing, and a full multigrid method. The Baldwin-Lomax eddy viscosity model is used for turbulence closure. A zonal, nonperiodic grid is used to minimize mesh distortion in and downstream of the throat region. Applications are presented for an annular vane with and without end wall contouring, and for a large scale linear cascade. The calculation is validated by comparing with experiments and by studying grid dependency.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TM-105257 , ICOMP-91-18 , E-6587 , NAS 1.15:105257
    Format: application/pdf
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  • 14
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    Validation of viscous and inviscid computational methods for turbomachinery components (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An assessment of several three-dimensional computer codes used at the NASA Lewis Research Center is presented. Four flow situations are examined, for which both experimental data and computational results are available. The four flows form a basis for the evaluation of the computational procedures. It is concluded that transonic rotor flow at peak efficiency conditions may be calculated with a reasonable degree of accuracy, whereas, off-design conditions are not accurately determined. Duct flows and turbine cascade flows may also be computed with reasonable accuracy whereas radial inflow turbine flow remains a challenging problem.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-42
    Format: text
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  • 15
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    Computation of three-dimensional, rotational flow through turbomachinery blade rows for improved aerodynamic design studies (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The performance of a three dimensional computer code developed for predicting the flowfield in stationary and rotating turbomachinery blade rows is described in this study. The four stage Runge-Kutta numerical integration scheme is used for solving the governing flow equations and yields solution to the full, three dimensional, unsteady Euler equations in cylindrical coordinates. This method is fully explicit and uses the finite volume, time marching procedure. In order to demonstrate the accuracy and efficiency of the code, steady solutions were obtained for several cascade geometries under widely varying flow conditions. Computed flowfield results are presented for a fully subsonic turbine stator and a low aspect ratio, transonic compressor rotor blade under maximum flow and peak efficiency design conditions. Comparisons with Laser Anemometer measurements and other numerical predictions are also provided to illustrate that the present method predicts important flow features with good accuracy and can be used for cost effective aerodynamic design studies.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-26
    Format: text
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  • 16
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    Validation of viscous and inviscid computational methods for turbomachinery components (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An assessment of several three-dimensional computer codes used at the NASA Lewis Research Center is presented. Four flow situations are examined, for which both experimental data and computational results are available. The four flows form a basis for the evaluation of the computational procedures. It is concluded that transonic rotor flow at peak efficiency conditions may be calculated with a reasonable degree of accuracy, whereas, off-design conditions are not accurately determined. Duct flows and turbine cascade flows may also be computed with reasonable accuracy whereas radial inflow turbine flow remains a challenging problem.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87193 , E-2765 , NAS 1.15:87193 , International Gas Turbine Conference; Dusseldorf; Germany
    Format: application/pdf
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  • 17
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    A study of composite solid-propellant flame structure using a spectral radiation shadowgraph technique. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-05-24
    Description: Composite solid propellant flame structure in vicinity of burning surface based on spectral radiation shadowgraph technique
    Keywords: PROPELLANTS
    Type: AIAA PAPER 65-60
    Format: text
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  • 18
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    EFFECT OF OXIDIZER PARTICLE SIZE ON ADDITIVE AGGLOMERATION (1962)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Effect of oxidizer particle size on additive agglomeration
    Keywords: PHYSICS, PLASMA
    Type: NASA-TN-D-1438
    Format: application/pdf
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  • 19
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    The origin of spurious solutions in computational electromagnetics (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The origin of spurious solutions in computational electromagnetics, which violate the divergence equations, is deeply rooted in a misconception about the first-order Maxwell's equations and in an incorrect derivation and use of the curl-curl equations. The divergence equations must be always included in the first-order Maxwell's equations to maintain the ellipticity of the system in the space domain and to guarantee the uniqueness of the solution and/or the accuracy of the numerical solutions. The div-curl method and the least-squares method provide rigorous derivation of the equivalent second-order Maxwell's equations and their boundary conditions. The node-based least-squares finite element method (LSFEM) is recommended for solving the first-order full Maxwell equations directly. Examples of the numerical solutions by LSFEM for time-harmonic problems are given to demonstrate that the LSFEM is free of spurious solutions.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TM-106921 , E-9633 , ICOMP-95-8 , NAS 1.15:106921
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  • 20
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    One-dimensional nonlinear model for determining combustion instability in solid propellant rocket motors (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Nonlinear analysis of combustion instability in solid propellant rocket engines
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-3410
    Format: application/pdf
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