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  • 1980-1984  (9)
  • 1
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    EET theoretical design techniques (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: As a part of the EET aerodynamics program an out-of-house program was developed and monitored to provide theoretical procedures useful in the design of transport aircraft. The focus of the effort was to provide tools valid in the nonlinear transonic speed range. The effort was divided into two basic areas, inviscid configuration analysis and design procedures and viscous correction procedures.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advan. Aerodyn.: Selected NASA Res.; p 79-94
    Format: text
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  • 2
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    A strongly implicit procedure for the compressible Navier-Stokes equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The strongly implicit procedure of Stone is used to obtain numerical solutions of the compressible Navier-Stokes equations in conservative form. In contrast to the spatially split Douglas-Gunn type methods, the method is shown to be numerically stable for the three-dimensional wave equation. The method is applied to a variety of external and internal two-dimensional flow problems involving shock wave boundary-layer interaction for both laminar and turbulent flows. The results are in good agreement with other methods and/or experiments. The storage penalty associated with the method is discussed and a simple, yet effective, means of minimizing the problem is presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 84-0424
    Format: text
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  • 3
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    Vectorized schemes for conical potential flow using the artificial density method (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A method is developed to determine solutions to the full-potential equation for steady supersonic conical flow using the artificial density method. Various update schemes used generally for transonic potential solutions are investigated. The schemes are compared for speed and robustness. All versions of the computer code have been vectorized and are currently running on the CYBER-203 computer. The update schemes are vectorized, where possible, either fully (explicit schemes) or partially (implicit schemes). Since each version of the code differs only by the update scheme and elements other than the update scheme are completely vectorizable, comparisons of computational effort and convergence rate among schemes are a measure of the specific scheme's performance. Results are presented for circular and elliptical cones at angle of attack for subcritical and supercritical crossflows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0162
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  • 4
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    Temporal and spatial inconsistencies of time-split finite-difference schemes (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The properties of an implicit time-split algorithm, which utilizes locally one dimensional spatial steps, are examined using the two-dimensional heat conduction equation as the test problem. Both temporal and spatial inconsistencies inherent in the scheme are identified. A consistent, implicit splitting approach is developed. The relationship between this method and other time-split implicit schemes is explained, and stability problems encountered with the method in three dimensions are discussed.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TP-1790 , L-13941
    Format: application/pdf
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  • 5
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    Velocity-split Navier-Stokes solution procedure for incompressible high Reynolds number external flows (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for solving the Navier-Stokes equations based on splitting the velocity vector into its rotational and irrotational parts was sucessfully applied to internal flow computations. The applicability of the method to external flows is examined by studying several model problems. The model problems are those of laminar and turbulent incompressible flow past a semi-infinite flat plate and laminar incompressible flow past a finite flat plate. For these problems, the procedure accurately reproduces the known solutions and is computationally very efficient even at high Reynolds numbers. Computational aspects of the method are discussed along with the possibility of using the procedure to retrofit a viscous capability into existing potential flow codes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1655 , L-13343
    Format: application/pdf
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  • 6
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    Flow through the tile gaps in the Space Shuttle Thermal Protection System (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of predicting aerodynamic loads on the insulating tiles of the Space Shuttle Thermal Protection System (TPS) is discussed and seen to require a method for predicting pressure and mass flux in the gaps between tiles. A mathematical model of the tile-gap flow is developed based upon a slow viscous (Stokes) flow analysis and is verified against available experimental data. This model derives the tile-gap pressure field from a solution of the two-dimensional Laplace equation; the mass flux vector is then calculated from the pressure gradient. The means for incorporating this model into a lumped-parameter network analogy for porous-media flow is also given. The flow model shows tile-gap mass flux to be very sensitive to the gap width indicating a need for coupling the TPS flow and tile displacement calculations. Finally recommendations are made concerning additional analytical and experimental work to improve TPS flow predictions.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-0001 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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  • 7
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    Improving the convergence rate of parabolic ADI methods (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The rate of convergence to steady state of parabolic Alternating Direction Implicit (ADI) solvers is analyzed in terms of the L(2)-norms of the residuals. The analysis allows one to predict the number of iterations necessary for convergence as function of the Courant number, Lambda. A simple modification of existing ADI codes is devised. It improves the convergence rate substantially and is insensitive to the Courant number in a large range of Lambda.
    Keywords: NUMERICAL ANALYSIS
    Type: AIAA PAPER 83-1897 , Computational Fluid Dynamics Conference; Jul 13, 1983 - Jul 15, 1983; Danvers, MA
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  • 8
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    A title-gap flow model for use in aerodynamic loads assessment of space shuttle thermal protection system: Parallel gap faces (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The problem of predicting aerodynamic loads on the insulating tiles of the space shuttle thermal protection system (TPS) is discussed and seen to require a method for predicting pressure and mass flux in the gaps between tiles. A mathematical model of the tile-gap flow is developed, based upon a slow viscous (Stokes) flow analysis, and is verified against experimental data. The tile-gap pressure field is derived from a solution of the two-dimensional Laplace equation; the mass-flux vector is then calculated from the pressure gradient. The means for incorporating this model into a lumped-parameter network analogy for porous-media flow is given. The means for incorporating this model into a lumped-parameter network analogy for porous-media flow is given. The flow model shows tile-gap mass flux to be very sensitive to the gap width indicating a need for coupling the TPS flow and tile displacement calculation. Analytical and experimental work to improve TPS flow predictions and a possible shuttle TPS hardware modification are recommended.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-83151
    Format: application/pdf
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  • 9
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    Accuracy and stability of time-split finite-difference schemes (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In a recently published work by Abarbanel and Gottlieb (1980), a new class of explicit time-split algorithms designed for application to the compressible Navier-Stokes equations was developed. These algorithms, which utilize locally-one-dimensional (LOD) spatial steps, were shown to possess stability characteristics superior to those of other time-split schemes. In the present work, the properties of an implicit LOD method, analogous to the Abarbanel-Gottlieb algorithm, are examined using the two-dimensional heat conduction equation as the test problem. Both temporal and spatial inconsistencies inherent in the scheme are identified, and a new consistent, implicit splitting approach is developed and applied to the linear Burgers' equation. The relationship between this new method and other time-split implicit schemes is explained and stability problems encountered with the method in three dimensions are discussed.
    Keywords: NUMERICAL ANALYSIS
    Type: AIAA PAPER 81-1005 , Computational Fluid Dynamics Conference; Jun 22, 1981 - Jun 23, 1981; Palo Alto, CA
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