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  • 1
    Electronic Resource
    Electronic Resource
    Numerical solutions for supersonic corner flow
    Amsterdam : Elsevier
    Journal of Computational Physics 17 (1975), S. 160-180 
    Details
    ISSN: 0021-9991
    Source: Elsevier Journal Backfiles on ScienceDirect 1907 - 2002
    Topics: Computer Science , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1016/0021-9991(75)90034-0
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Numerical solutions for supersonic corner flow (1975)
    Elsevier
    Details
    Publication Date: 1975-02-01
    Print ISSN: 0021-9991
    Electronic ISSN: 1090-2716
    Topics: Computer Science , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    MULTISHOCKED,THREE-DIMENSIONAL SUPERSONIC FLOWFIELDS WITH REAL GAS EFFECTS (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This program determines the supersonic flowfield surrounding three-dimensional wing-body configurations of a delta wing. It was designed to provide the numerical computation of three dimensional inviscid, flowfields of either perfect or real gases about supersonic or hypersonic airplanes. The governing equations in conservation law form are solved by a finite difference method using a second order noncentered algorithm between the body and the outermost shock wave, which is treated as a sharp discontinuity. Secondary shocks which form between these boundaries are captured automatically. The flowfield between the body and outermost shock is treated in a shock capturing fashion and therefore allows for the correct formation of secondary internal shocks . The program operates in batch mode, is in CDC update format, has been implemented on the CDC 7600, and requires more than 140K (octal) word locations.
    Keywords: AERODYNAMICS
    Type: ARC-11015
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Multidisciplinary computational aerosciences (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: By combining CFD with the computational state-of-the-art in structural mechanics, propulsion, aeroacoustics, electromagnetics, etc., multidisciplinary computational aerosciences (MCAS) poses a formidable computational challenge requiring the use of massively parallel machines. Research efforts must accordingly be directed to three areas: (1) parallel architectures, (2) systems software, and (3) applications software; attention is presently given to the last of these, in view of developments at NASA-Ames in solution methodology, physical modeling, and multidisciplinary validation experiments.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: Computing Systems in Engineering (ISSN 0956-0521); 3; 1-4; p. 87-95.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Numerical solutions for the complete shock wave structure behind supersonic edge delta wings (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Computerized simulation of shock waves and flow fields behind supersonic edge delta wings and wing-body combinations
    Keywords: AIRCRAFT
    Type: 3D CONF. ON SONIC BOOM RES. 1971; P 17-25
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Viscous transonic flow computation over Space Shuttle configuration (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A thin-layer Navier-Stokes code capable of predicting steady-state viscous flows is applied to the transonic flow over a Space Shuttle configuration. The code is written in the generalized coordinate system, and the grid-generation code of Fujii (1983) is used for the discretization of the flow field. The flow-field computation is done using the CRAY 1S computer at NASA Ames. The computed result is physically reasonable, even though no experimental data is available for the comparison purpose.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A perspective of theoretical and applied computational fluid dynamics (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 23; 328-341
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Numerical solutions for supersonic corner flow (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Analytical solutions for inviscid supersonic corner flows are virtually nonexistent due to the complexity of the interference geometry. In view of this, numerical solutions for swept-compressive and swept-expansive corner flows are obtained. The governing equations are written in strong conservation-law form and are solved iteratively in nonorthogonal conical coordinates by use of a second-order, shock-capturing, finite-difference technique. The computed wave structure and surface pressure distributions are compared with high Reynolds number experimental data and show very good agreement. The results clearly show that supersonic corner flow at reasonably high Reynolds numbers including the effect of sweep is dominated by the inviscid field.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics; 17; Feb. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Computation of three-dimensional, inviscid supersonic flows (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The paper sets forth in detail a method for the finite-difference computation of three-dimensional supersonic fields in an Eulerian mesh. First-, second-, and third-order finite difference schemes are examined. Attention is given to proper treatment of the impermeable and permeable boundaries encompassing the computational plane. Numerical results are presented for certain specific configurations: a conical wing-body combination, internal corner flow, a two-dimensional blunt body, an interfering shock problem, and three-dimensional inviscid supersonic flow past a shuttle-orbiter type vehicle.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Application of shock capturing and characteristics methods to shuttle flow fields (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The calculation of real gas flows around the space shuttle vehicle can be accomplished by the method of characteristics (MOC) or shock capture technique (SCT). Results obtained with these methods for an early orbiter shape proposed by the North American Rockwell Corporation and also for the more recent 040A configuration suggested by NASA-MSC are presented. Results obtained with the SCT code demonstrate its three-dimensional, multiple shock capturing capability while results obtained with the MOC code demonstrate the calculation of equilibrium real gas flows and the determination of flow variables required for a heating analysis.
    Keywords: FLUID MECHANICS
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 1; p 65-92
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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