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  • 1
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    Shock-capturing technique for hypersonic, chemically relaxing flows (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 481-488
    Format: text
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  • 2
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    Automatic multi-block grid generation for high-lift configuration wings (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A new method for automatic multi-block grid generation is described. The method combines the Modified Advancing Front Method as a Predictor with an elliptic scheme as a corrector. It advances a collection of cells by one cell height in the outward direction using Modified Advancing Front Method, and then corrects newly-obtained cell positions by solving elliptic equations. This predictor-corrector type scheme is repeatedly applied until the field of interest is filled with hexahedral grid cells. Given the configuration surface grid, the scheme produces block layouts as well as grid cells with overall smoothness as its output. The present method saves human-time and reduces the burden on the user in generating grids for general 3-D configurations. It was used to generate multi-block grids for wings in their high-lift configuration.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Lewis Research Center, Surface Modeling, Grid Generation, and Related Issues in Computational Fluid Dynamic (CFD) Solutions; p 671-688
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  • 3
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    Development of an Automatic Grid Generator for Multi-Element High-Lift Wings (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The procedure to generate the grid around a complex wing configuration is presented in this report. The automatic grid generation utilizes the Modified Advancing Front Method as a predictor and an elliptic scheme as a corrector. The scheme will advance the surface grid one cell outward and the newly obtained grid is corrected using the Laplace equation. The predictor-corrector step ensures that the grid produced will be smooth for every configuration. The predictor-corrector scheme is extended for a complex wing configuration. A new technique is developed to deal with the grid generation in the wing-gaps and on the flaps. It will create the grids that fill the gap on the wing surface and the gap created by the flaps. The scheme recognizes these configurations automatically so that minimal user input is required. By utilizing an appropriate sequence in advancing the grid points on a wing surface, the automatic grid generation for complex wing configurations is achieved.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-204631 , NAS 1.26:204631
    Format: application/pdf
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  • 4
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    Dual-Code Solution Strategy for Chemically-Reacting Hypersonic Flows (1995)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A new procedure seeks to combine the thin-layer Navier-Stokes solver LAURA with the parabolized Navier-Stokes solver UPS for the aerothermodynamic solution of chemically-reacting air flow fields. The interface protocol is presented and the method is applied to two slender, blunted shapes. Both axisymmetric and three-dimensional solutions are included with surface pressure and heat transfer comparisons between the present method and previously published results. The case of Mach 25 flow over an axisymmetric six degree sphere-cone with a non-catalytic wall is considered to 100 nose radii. A stability bound on the marching step size was observed with this case and is attributed to chemistry effects resulting from the non-catalytic wall boundary condition. A second case with Mach 28 flow over a sphere-cone-cylinder-flare configuration is computed at both two and five degree angles of attack with a fully-catalytic wall. Surface pressures are seen to be within five percent with the present method compared to the baseline LAURA solution and heat transfers are within 10 percent. The effect of grid resolution is investigated in both the radial and streamwise directions. The procedure demonstrates significant, order of magnitude reductions in solution time and required memory for the three-dimensional case in comparison to an all thin-layer Navier-Stokes solution.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 5
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    Development of an automatic block generation algorithm (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for automatic multiblock grid generation is described. The method combines the modified advancing front method as a predictor with an elliptic scheme as a corrector. It advances a collection of cells by one cell height in the outward direction using modified advancing front method, and then corrects newly-obtained cell positions by solving elliptic equations. This predictor-corrector type scheme is repeatedly applied until the field of interest is filled with hexahedral grid cells. Given the configuration surface grid, the scheme produces block layouts as well as grid cells with overall smoothness as its output. The method saves human-time and reduces the burden on the user in generating grids for general 3D configurations. It is used to generate multiblock grids for wings in their high-lift configuration.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-199546 , NIPS-95-05582 , NAS 1.26:199546
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  • 6
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    A diagonal implicit scheme for computing flows with finite-rate chemistry (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new algorithm for solving steady, finite-rate chemistry, flow problems is presented. The new scheme eliminates the expense of inverting large block matrices that arise when species conservation equations are introduced. The source Jacobian matrix is replaced by a diagonal matrix which is tailored to account for the fastest reactions in the chemical system. A point-implicit procedure is discussed and then the algorithm is included into the LU-SGS scheme. Solutions are presented for hypervelocity reentry and Hydrogen-Oxygen combustion. For the LU-SGS scheme a CFL number in excess of 10,000 has been achieved.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: AIAA PAPER 90-1577
    Format: text
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  • 7
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    Nonequilibrium thermo-chemical calculations using a diagonal implicit scheme (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A recently developed computer program for hypersonic vehicle flow analysis is described. The program uses a diagonal implicit algorithm to solve the equations of viscous flow for a gas in thermochemical nonequilibrium. The diagonal scheme eliminates the expense of inverting large block matrices that arise when species conservation equations are introduced. The program uses multiple zones of grids patched together and includes radiation wall and rarefied gas boundary conditions. Solutions are presented for hypersonic flows of air and hydrogen air mixtures.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-0468
    Format: text
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  • 8
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    Diagonal implicit scheme for computing flows with finite rate chemistry (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 6; 208-216
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  • 9
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    Calculating Shocks In Chemically Reacting Flows (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Total-variation-diminishing dissipation operator results in crisp shocks. Report discusses method for numerical simulation of shocks in hypersonic, chemically reacting flows. Introduces mathematical model of gas of as many as three species for which species-conservation equations coupled with gas-dynamic equations.
    Keywords: PHYSICAL SCIENCES
    Type: ARC-11747 , NASA Tech Briefs (ISSN 0145-319X); 17; 4; P. 50
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  • 10
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    Calculating Shocks In Flows At Chemical Equilibrium (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Boundary conditions prove critical. Conference paper describes algorithm for calculation of shocks in hypersonic flows of gases at chemical equilibrium. Although algorithm represents intermediate stage in development of reliable, accurate computer code for two-dimensional flow, research leading up to it contributes to understanding of what is needed to complete task.
    Keywords: PHYSICAL SCIENCES
    Type: ARC-11741 , NASA Tech Briefs (ISSN 0145-319X); 12; 9; P. 64
    Format: text
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