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  • 1
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    The 3D Euler solutions using automated Cartesian grid generation (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Viewgraphs on 3-dimensional Euler solutions using automated Cartesian grid generation are presented. Topics covered include: computational fluid dynamics (CFD) and the design cycle; Cartesian grid strategy; structured body fit; grid generation; prolate spheroid; and ONERA M6 wing.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Langley Research Center, Unstructured Grid Generation Techniques and Software; p 251-260
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Transonic and supersonic Euler computations of vortex-dominated flow fields about a generic fighter (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flow fields about a generic flighter model were computed using FL057, a 3-D, finite volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers (0.6, 0.8, 1.2, 1.4, and 1.6) are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing-body and a wing-body-chine. FL057 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FL057 predictions were also accurate for some test conditions once the leading edge vortex became well established. At the subsonic speeds, FL057 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3156 , A-90161 , NAS 1.60:3156
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    EGADS: A microcomputer program for estimating the aerodynamic performance of general aviation aircraft (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: EGADS is a comprehensive preliminary design tool for estimating the performance of light, single-engine general aviation aircraft. The software runs on the Apple Macintosh series of personal computers and assists amateur designers and aeronautical engineering students in performing the many repetitive calculations required in the aircraft design process. The program makes full use of the mouse and standard Macintosh interface techniques to simplify the input of various design parameters. Extensive graphics, plotting, and text output capabilities are also included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104013 , A-93066 , NAS 1.15:104013
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    3D automatic Cartesian grid generation for Euler flows (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: We describe a Cartesian grid strategy for the study of three dimensional inviscid flows about arbitrary geometries that uses both conventional and CAD/CAM surface geometry databases. Initial applications of the technique are presented. The elimination of the body-fitted constraint allows the grid generation process to be automated, significantly reducing the time and effort required to develop suitable computational grids for inviscid flowfield simulations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3386 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 2 (A93-44994 18-34); p. 959-969.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Unstructured Euler flow solutions using hexahedral cell refinement (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An attempt is made to extend grid refinement into three dimensions by using unstructured hexahedral grids. The flow solver is developed using the TIGER (topologically Independent Grid, Euler Refinement) as the starting point. The program uses an unstructured hexahedral mesh and a modified version of the Jameson four-stage, finite-volume Runge-Kutta algorithm for integration of the Euler equations. The unstructured mesh allows for local refinement appropriate for each freestream condition, thereby concentrating mesh cells in the regions of greatest interest. This increases the computational efficiency because the refinement is not required to extend throughout the entire flow field.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0637
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    A transonic/supersonic CFD analysis of a generic fighter (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Flow fields about a generic fighter model have been computed using FLO57, a three-dimensional, finite-volume Euler code. Computed pressure coefficients, forces, and moments at several Mach numbers - 0.6, 0.8, 1.2, 1.4, and 1.6 - are compared with wind tunnel data over a wide range of angles of attack in order to determine the applicability of the code for the analysis of fighter configurations. Two configurations were studied, a wing/body and a wing/body/chine. FLO57 predicted pressure distributions, forces, and moments well at low angles of attack, at which the flow was fully attached. The FLO57 predictions were also accurate for some test conditions once the leading-edge vortex became well established. At the subsonic speeds, FLO57 predicted vortex breakdown earlier than that seen in the experimental results. Placing the chine on the forebody delayed the onset of bursting and improved the correlation between numerical and experimental data at the subsonic conditions.
    Keywords: AERODYNAMICS
    Type: ICAS Congress; Sept. 9-14, 1990; Stockholm; Sweden
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    3D Euler flow solutions using unstructured Cartesian and prismatic grids (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A hyperbolic prismatic grid generation technique is combined with a background Cartesian grid for the study of inviscid three-dimensional flows. The mathematics of the hyperbolic prismatic grid generation algorithm are described, and some simple inviscid demonstration cases are presented. By combining the simplicity of the Cartesian background grid with the geometric flexibility and computational efficiencies inherent to prismatic grids, this approach shows promise for improving computational aerodynamic simulations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0331 , ; 12 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Development and Applications of 3D Cartesian CFD Technology (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The urgent need for dramatic reductions in aircraft design cycle time is focusing scrutiny upon all aspects of computational fluid dynamics (CFD). These reductions will most likely come not from increased reliance upon user-interactive (and therefore time-expensive) methods, but instead from methods that can be fully automated and incorporated into 'black box' solutions. In comparison with tetrahedral methods, three-dimensional Cartesian grid approaches are in relative infancy, but initial experiences with automated Cartesian techniques are quite promising. Our research is targeted at furthering the development of Cartesian methods so that they can become key elements of a completely automatic grid generation/flow solution procedure applicable to the Euler analysis of complex aircraft geometries.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA Lewis Surface Modeling and Grid Generation Workshop; May 09, 1995 - May 11, 1995; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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