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  • 1
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    Status of CFD for LaRC's HSR high-lift program (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The viewgraphs for a status report for using computational fluid dynamics (CFD) for NASA Langley's Research Center High Speed Research High-Lift Program are provided. The objectives of CFD applications, the approach to developing appropriate CFD codes, and the dominant flow mechanisms are outlined. Possible CFD codes are compared; graphs comparing force coefficients, surface pressure distribution, and force are included. The plans for using CFD applications are listed.
    Keywords: AERODYNAMICS
    Type: First Annual High-Speed Research Workshop, Part 4; p 1695-1717
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Computational fluid dynamics research and applications at NASA Langley Research Center (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Information on computational fluid dynamics (CFD) research and applications carried out at the NASA Langley Research Center is given in viewgraph form. The Langley CFD strategy, the five-year plan in CFD and flow physics, 3-block grid topology, the effect of a patching algorithm, F-18 surface flow, entropy and vorticity effects that improve accuracy of unsteady transonic small disturbance theory, and the effects of reduced frequency on first harmonic components of unsteady pressures due to airfoil pitching are among the topics covered.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 1: Sessions 1-6; p 35-47
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Finite-volume scheme for transonic potential flow about airfoils and bodies in an arbitrarily shaped channel (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A conservative finite-volume difference scheme is developed for the potential equation to solve transonic flow about airfoils and bodies in an arbitrarily shaped channel. The scheme employs a mesh which is a nearly conformal O mesh about the airfoil and nearly orthogonal at the channel walls. The mesh extends to infinity upstream and downstream, where the mapping is singular. Special procedures are required to treat the singularities at infinity, including computation of the metrics near those points. Channels with exit areas different from inlet areas are solved; a body with a sting mount is an example of such a case.
    Keywords: AERODYNAMICS
    Type: Langley Symposium on Aerodynamics, Volume 1; p 25-43
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Computational mechanics and physics at NASA Langley Research Center (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An overview is given of computational mechanics and physics at NASA Langley Research Center. Computational analysis is a major component and tool in many of Langley's diverse research disciplines, as well as in the interdisciplinary research. Examples are given for algorithm development and advanced applications in aerodynamics, transition to turbulence and turbulence simulation, hypersonics, structures, and interdisciplinary optimization.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA. Ames Research Center, Supercomputing in Aerospace; p 23-33
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    ICASE/LaRC Workshop on Adaptive Grid Methods (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Solution-adaptive grid techniques are essential to the attainment of practical, user friendly, computational fluid dynamics (CFD) applications. In this three-day workshop, experts gathered together to describe state-of-the-art methods in solution-adaptive grid refinement, analysis, and implementation; to assess the current practice; and to discuss future needs and directions for research. This was accomplished through a series of invited and contributed papers. The workshop focused on a set of two-dimensional test cases designed by the organizers to aid in assessing the current state of development of adaptive grid technology. In addition, a panel of experts from universities, industry, and government research laboratories discussed their views of needs and future directions in this field.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CP-3316 , NAS 1.55:3316 , L-17539 , NIPS-96-07318 , Nov 07, 1994 - Nov 09, 1994; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Application of Dorodnitsyn's Integral Method to Nonequilibrium Flows over Pointed Bodies (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Dorodnitsyn's integral method is used to obtain an approximate solution to the supersonic nonequilibrium flow over pointed bodies with attached shock waves. The partial differential equations governing the flow are converted to an approximate set of ordinary equations, which are solved by numerical integration starting at the body tip. Detailed analytical and numerical results for the first approximation are presented, considering the vibrational relaxation of a diatomic gas over a wedge or cone. It is shown that the first approximation yields: (1) The exact flow-variable gradients at the wedge tip (2) Expressions for the flow-variable gradients at the cone tip which are in agreement with extrapolations of characteristics calculations (3) A good approximate algebraic solution for frozen or equilibrium conical flow (4) An approximate expression for the nonequilibrium-flow stream function which affords a means of obtaining variations across the shock layer of the temperature and vibrational energy. Numerical results for both the wedge and cone compare favorably with identical cases computed by the method of characteristics.
    Keywords: Aerodynamics
    Type: NASA-TN-D-1942
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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