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  • 1
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    General Dynamics' perspective on CFD code calibration/validation (1987)
    In:  CASI
    Details
    Publication Date: 2006-06-13
    Description: Information is given in viewgraph form on General Dynamics' perspective on computational fluid dynamics (CFD) code calibration and validation. Topics covered include a hypersonic blunted cone, a hypersonic wedge/cylinder, a wing vortex defined by Mach contours, pressure distributions, and 3D turbulent flow behind a 2D flat plate as measured in a water tunnel with a laser Doppler velocimeter.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Research Center, NASA CFD Validation Workshop; p 559-577
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Remarks on future computational aerodynamics requirements (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The development of upgraded and expanded computational aerodynamics methods for the design and analysis of aircraft configurations should be performed by both government and industry to ensure that the objectives for aircraft design are satisfied from both the industrial competitive design standpoint and from the government standpoint. Any programs developed must be heavily user-oriented and provide maximum visibility and creditability to management. Early consideration should be given to the adequate management of such a facility when it becomes available.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 91-101
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Computational fluid dynamics: Transition to design applications (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The development of aerospace vehicles, over the years, was an evolutionary process in which engineering progress in the aerospace community was based, generally, on prior experience and data bases obtained through wind tunnel and flight testing. Advances in the fundamental understanding of flow physics, wind tunnel and flight test capability, and mathematical insights into the governing flow equations were translated into improved air vehicle design. The modern day field of Computational Fluid Dynamics (CFD) is a continuation of the growth in analytical capability and the digital mathematics needed to solve the more rigorous form of the flow equations. Some of the technical and managerial challenges that result from rapidly developing CFD capabilites, some of the steps being taken by the Fort Worth Division of General Dynamics to meet these challenges, and some of the specific areas of application for high performance air vehicles are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Research Center, Supercomputing in Aerospace; p 69-76
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The application of CFD for military aircraft design at transonic speeds (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Numerous computational fluid dynamics (CFD) codes are available that solve any of several variations of the transonic flow equations from small disturbance to full Navier-Stokes. The design philosophy at General Dynamics Fort Worth Division involves use of all these levels of codes, depending on the stage of configuration development. Throughout this process, drag calculation is a central issue. An overview is provided for several transonic codes and representative test-to-theory comparisons for fighter-type configurations are presented. Correlations are shown for lift, drag, pitching moment, and pressure distributions. The future of applied CFD is also discussed, including the important task of code validation. With the progress being made in code development and the continued evolution in computer hardware, the routine application of these codes for increasingly more complex geometries and flow conditions seems apparent.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1; p 109-132
    Format: application/pdf
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  • 5
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    Application of the vortex-lattice technique to the analysis of thin wings with vortex separation and thick multi-element wings (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two techniques for extending the range of applicability of the basic vortex-lattice method are discussed. The first improves the computation of aerodynamic forces on thin, low-aspect-ratio wings of arbitrary planforms at subsonic Mach numbers by including the effects of leading-edge and tip vortex separation, characteristic of this type wing, through use of the well-known suction-analogy method of E. C. Polhamus. Comparisons with experimental data for a variety of planforms are presented. The second consists of the use of the vortex-lattice method to predict pressure distributions over thick multi-element wings (wings with leading- and trailing-edge devices). A method of laying out the lattice is described which gives accurate pressures on the top and part of the bottom surface of the wing. Limited comparisons between the result predicted by this method, the conventional lattice arrangement method, experimental data, and 2-D potential flow analysis techniques are presented.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Vortex-Lattice Utilization; p 237-260
    Format: application/pdf
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  • 6
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    Theoretical evaluation of a V/STOL fighter model utilizing the PAN AIR code (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The PAN AIR computer code was investigated as a tool for predicting closely coupled aerodynamic and propulsive flowfields of arbitrary configurations. The NASA/Ames V/STOL fighter model, a configuration of complex geometry, was analyzed with the PAN AIR code. A successful solution for this configuration was obtained when the nozzle exit was treated as an impermeable surface and no wakes were included around the nozzle exit. When separated flow was simulated from the end of the nacelle, requiring the use of wake networks emanating from the nozzle exit, a number of problems were encountered. A circular body nacelle model was used to investigate various techniques for simulating the exhaust plume in PAN AIR. Several approaches were tested and eliminated because they could not correctly simulate the interference effects. Only one plume modeling technique gave good results. A PAN AIR computation that used a plume shape and inflow velocities obtained from the Navier-Stokes solution for the plume produced results for the effects of power that compared well with experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166395 , NAS 1.26:166395
    Format: application/pdf
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  • 7
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    Aerodynamic characteristics of forebody and nose strakes based on F-16 wind tunnel test experience. Volume 2: Data base (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The YF-16 and F-16 developmental wind tunnel test program was reviewed and all force data pertinent to the design of forebody and nose strakes extracted. A complete set of these data is presented without analysis.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-158922
    Format: application/pdf
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  • 8
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    Development of V/STOL methodology based on a higher order panel method (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of a computational technique to predict the complex flowfields of V/STOL aircraft was initiated in which a number of modules and a potential flow aerodynamic code were combined in a comprehensive computer program. The modules were developed in a building-block approach to assist the user in preparing the geometric input and to compute parameters needed to simulate certain flow phenomena that cannot be handled directly within a potential flow code. The PAN AIR aerodynamic code, which is higher order panel method, forms the nucleus of this program. PAN AIR's extensive capability for allowing generalized boundary conditions allows the modules to interact with the aerodynamic code through the input and output files, thereby requiring no changes to the basic code and easy replacement of updated modules.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166491 , NAS 1.26:166491
    Format: application/pdf
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