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  • 1
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    Numerical aerodynamic simulation of the space shuttle ascent environment (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: After the STS 51-L accident, an extensive review of the Space Shuttle Orbiter's ascent aerodynamic loads uncovered several questionable areas that required further analysis. The insight gained by comparing the Shuttle ascent CFD numerical simulations, obtained by the NASA Ames Space Shuttle Flow Simulation Group, to the current IVBC-3 aerodynamic loads database was instrumental in resolving uncertainties on the Orbiter payload bay doors and fuselage. Initial confidence in the numerical simulations was gained by comparing them with the limited flight data that had been obtained during the Orbiter Flight Test (OFT) program. Current CFD results exist for Mach numbers 0.6, 0.9, 1.05, 1.55, 2.0, and 2.5. Since the pre STS-1 wind tunnel test program (IA-105) often yields considerable differences when compared to STS-5 flight data, the M(sub infinity) = 1.05 transonic case is the most investigated. The IA308 mated-vehicle hot gas plume wind tunnel test, recently completed at AEDC 16T (transonic) and Lewis (hypersonic), is also used to compare with the computation where applicable.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12; p 117-131
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    On automating domain connectivity for overset grids (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An alternative method for domain connectivity among systems of overset grids is presented. Reference uniform Cartesian systems of points are used to achieve highly efficient domain connectivity, and form the basis for a future fully automated system. The Cartesian systems are used to approximate body surfaces and to map the computational space of component grids. By exploiting the characteristics of Cartesian systems, Chimera type hole-cutting and identification of donor elements for intergrid boundary points can be carried out very efficiently. The method is tested for a range of geometrically complex multiple-body overset grid systems. A dynamic hole expansion/contraction algorithm is also implemented to obtain optimum domain connectivity; however, it is tested only for geometry of generic shapes.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-199522 , NAS 1.26:199522 , OMI-04-92-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    User interface user's guide for HYPGEN (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The user interface (UI) of HYPGEN is developed using Panel Library to shorten the learning curve for new users and provide easier ways to run HYPGEN for casual users as well as for advanced users. Menus, buttons, sliders, and type-in fields are used extensively in UI to allow users to point and click with a mouse to choose various available options or to change values of parameters. On-line help is provided to give users information on using UI without consulting the manual. Default values are set for most parameters and boundary conditions are determined by UI to further reduce the effort needed to run HYPGEN; however, users are free to make any changes and save it in a file for later use. A hook to PLOT3D is built in to allow graphics manipulation. The viewpoint and min/max box for PLOT3D windows are computed by UI and saved in a PLOT3D journal file. For large grids which take a long time to generate on workstations, the grid generator (HYPGEN) can be run on faster computers such as Crays, while UI stays at the workstation.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-190304 , NAS 1.26:190304 , REPT-92-008
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  • 4
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    Multiple-body simulation with emphasis on integrated Space Shuttle vehicle (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The program to obtain intergrid communications - Pegasus - was enhanced to make better use of computing resources. Periodic block tridiagonal and penta-diagonal diagonal routines in OVERFLOW were modified to use a better algorithm to speed up the calculation for grids with periodic boundary conditions. Several programs were added to collar grid tools and a user friendly shell script was developed to help users generate collar grids. User interface for HYPGEN was modified to cope with the changes in HYPGEN. ET/SRB attach hardware grids were added to the computational model for the space shuttle and is currently incorporated into the refined shuttle model jointly developed at Johnson Space Center and Ames Research Center. Flow simulation for the integrated space shuttle vehicle at flight Reynolds number was carried out and compared with flight data as well as the earlier simulation for wind tunnel Reynolds number.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-192289 , NAS 1.26:192289 , MCAT-93-004
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  • 5
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    On automating domain connectivity for overset grids (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An alternative method for domain connectivity among systems of overset grids is presented. Reference uniform Cartesian systems of points are used to achieve highly efficient domain connectivity, and form the basis for a future fully automated system. The Cartesian systems are used to approximated body surfaces and to map the computational space of component grids. By exploiting the characteristics of Cartesian Systems, Chimera type hole-cutting and identification of donor elements for intergrid boundary points can be carried out very efficiently. The method is tested for a range of geometrically complex multiple-body overset grid systems.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-CR-196113 , NAS 1.26:196113 , OMI-04-92-2
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  • 6
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    Navier-Stokes computations on full-span wing-body configuration with oscillating control surfaces (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Unsteady Navier-Stokes simulations have been performed for vortical flows over an 'arrow-wing' configuration of a supersonic transport in the transonic regime. Computed steady pressures and integrated force coefficients with and without control surface deflection at a moderate angle of attack are compared with experiment. For unsteady cases, oscillating trailing-edge control surfaces are modeled by using moving grids. Response characteristics between symmetric and anti-symmetric oscillatory motions of the control surfaces on the left and right wings are studied. The anti-symmetric case produces higher lift than the steady case with no deflection, and the unsteady symmetric case produces higher lift than the anti-symmetric case. The detailed analysis of the wake structure revealed a strong interaction between the primary vortex and the wake vortex sheet from the flap region when the flap is deflected up.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3687 , In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08); p. 555-565.
    Format: text
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  • 7
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    User's manual for the HYPGEN hyperbolic grid generator and the HGUI graphical user interface (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The HYPGEN program is used to generate a 3-D volume grid over a user-supplied single-block surface grid. This is accomplished by solving the 3-D hyperbolic grid generation equations consisting of two orthogonality relations and one cell volume constraint. In this user manual, the required input files and parameters and output files are described. Guidelines on how to select the input parameters are given. Illustrated examples are provided showing a variety of topologies and geometries that can be treated. HYPGEN can be used in stand-alone mode as a batch program or it can be called from within a graphical user interface HGUI that runs on Silicon Graphics workstations. This user manual provides a description of the menus, buttons, sliders, and typein fields in HGUI for users to enter the parameters needed to run HYPGEN. Instructions are given on how to configure the interface to allow HYPGEN to run either locally or on a faster remote machine through the use of shell scripts on UNIX operating systems. The volume grid generated is copied back to the local machine for visualization using a built-in hook to PLOT3D.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-108791 , A-93133 , NAS 1.15:108791
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  • 8
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    Navier-Stokes Computations on Full Wing-Body Configuration with Oscillating Control Surfaces (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Unsteady Navier-Stokes simulations have been performed for vortical flows over an "arrow-wing" configuration of a supersonic transport in the transonic regime. Computed steady pressures and integrated force coefficients with and without control surface deflection at a moderate angle of attack are compared with experiment. For unsteady cases, oscillating trailing-edge control surfaces are modeled by using moving grids. Response characteristics between symmetric and antisymmetric oscillatory motions of the control surfaces on the left and right wings are studied. The antisymmetric case produces higher lift than the steady case with no deflection and the unsteady symmetric case produces higher lift than the antisymmetric case. The detailed analysis of the wake structure revealed a strong interaction between the primary vortex and the wake vortex sheet from the flap region when the flap is deflected up.
    Keywords: Aerodynamics
    Type: NASA/TM-95-207298 , NAS 1.15:207298 , AIAA Paper 93-3687 , Atmospheric Flight Mechanics Conference; Aug 09, 1993 - Aug 11, 1993; Monterey, CA; United States|Journal of Aircraft; 32; 6; 1227-1233
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  • 9
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    Development of a large scale Chimera grid system for the Space Shuttle Launch Vehicle (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The application of CFD techniques to large problems has dictated the need for large team efforts. This paper offers an opportunity to examine the motivations, goals, needs, problems, as well as the methods, tools, and constraints that defined NASA's development of a 111 grid/16 million point grid system model for the Space Shuttle Launch Vehicle. The Chimera approach used for domain decomposition encouraged separation of the complex geometry into several major components each of which was modeled by an autonomous team. ICEM-CFD, a CAD based grid generation package, simplified the geometry and grid topology definition by provoding mature CAD tools and patch independent meshing. The resulting grid system has, on average, a four inch resolution along the surface.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 93-0533 , ; 14 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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