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  • 1
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    Improving the convergence rate to steady state of parabolic ADI methods (1986)
    Elsevier
    Details
    Publication Date: 1986-11-01
    Print ISSN: 0021-9991
    Electronic ISSN: 1090-2716
    Topics: Computer Science , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Computational fluid dynamics for hypersonic airbreathing aircraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A development status evaluation is presented for CFD methods applicable to fuselage-integrated scramjet powerplant incorporating hypersonic vehicles; these methods are critically important due to the unavailability of experimental facilities for such elevated Mach number/high-enthalphy conditions. Advancements are required in algorithm robustness and speed, geometric flexibility, and the inclusion of more complete flow physics. The most serious deficiencies lie in turbulence modeling, the lack of complete transition-prediction methods, and combustion modeling.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 1 (A93-42576 17-02); p. 55-71.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The new challenge of computational aeroscience (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This paper discusses NASA's Computational Aerosciences (CAS) Project of the High Performance Computing and Communications Program (HPCCP). The project is aimed at developing advanced, multidisciplinary simulation capabilities for aerospace vehicle and propulsion system design. It is also aimed at overcoming computational performance barriers by accelerating the development of parallel computer technology. The goals and approach of the CAS Project are described and the challenges to its implementation are addressed. Specific vehicle class simulations to be demonstrated and the principal mutidisciplinary modeling approaches to be emphasized are described. The computational speed and memory requirements for representative multidisciplinary applications are estimated. Finally, the state of parallel computer technology including programming issues and the results of performance measurements are explored.
    Keywords: AERODYNAMICS
    Type: In: ICAS, Congress, 18th, Beijing, China, Sept. 20-25, 1992, Proceedings. Vol. 1 (A93-14151 03-01); p. 83-96.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    High-speed code validation (1987)
    In:  CASI
    Details
    Publication Date: 2006-06-13
    Description: The topics are presented in viewgraph form and include the following: NFL body experiment; high-speed validation problems; 3-D Euler/Navier-Stokes inlet code; two-strut inlet configuration; pressure contours in two longitudinal planes; sidewall pressure distribution; pressure distribution on strut inner surface; inlet/forebody tests in 60 inch helium tunnel; pressure distributions on elliptical missile; code validations; small scale test apparatus; CARS nonintrusive measurements; optimized cone-derived waverider study; etc.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Research Center, NASA CFD Validation Workshop; p 210-243
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Retooling CFD for hypersonic aircraft (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The CFD facility requirements of hypersonic aircraft configuration design development are different from those thus far employed for reentry vehicle design, because (1) the airframe and the propulsion system must be fully integrated to achieve the desired performance; (2) the vehicle must be reusable, with minimum refurbishment requirements between flights; and (3) vehicle performance must be optimized for a wide range of Mach numbers. An evaluation is presently made of flow resolution within shock waves, transition and turbulence phenomenon tractability, chemical reaction modeling, and hypersonic boundary layer transition, with state-of-the-art CFD.
    Keywords: AERONAUTICS (GENERAL)
    Type: Aerospace America (ISSN 0740-722X); 25; 32-35
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    CFD propels NASP propulsion progress (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The most complex aerothermodynamics encountered in the National Aerospace Plane (NASP) propulsion system are associated with the fuel-mixing and combustion-reaction flows of its combustor section; adequate CFD tools must be developed to model shock-wave systems, turbulent hydrogen/air mixing, flow separation, and combustion. Improvements to existing CFD codes have involved extension from two dimensions to three, as well as the addition of finite-rate hydrogen-air chemistry. A novel CFD code for the treatment of reacting flows throughout the NASP, designated GASP, uses the most advanced upwind-differencing technology.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Aerospace America (ISSN 0740-722X); 28; 26
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Computational analysis of hypersonic airbreathing aircraft flow fields (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The general problem of calculating the flow fields associated with hypersonic airbreathing aircraft is presented. Unique aspects of hypersonic aircraft aerodynamics are introduced and their demands on computational fluid dynamics are outlined. Example calculations associated with inlet/forebody integration and hypersonic nozzle design are presented to illustrate the nature of the problems considered.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Research Center, Supercomputing in Aerocomputing; p 239-255
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Computational structural mechanics and fluid dynamics: Advances and trends; Proceedings of the Symposium, Washington, DC, Oct. 17-19, 1988 (1988)
    In:  Other Sources
    Details
    Publication Date: 2016-03-09
    Description: Recent advances in computational structural and fluid dynamics are discussed in reviews and reports. Topics addressed include fluid-structure interaction and aeroelasticity, CFD techniques for reacting flows, micromechanics, stability and eigenproblems, probabilistic methods and chaotic dynamics, and perturbation and spectral methods. Consideration is given to finite-element, finite-volume, and boundary-element methods; adaptive methods; parallel processing machines and applications; and visualization, mesh generation, and AI interfaces.
    Keywords: ENGINEERING (GENERAL)
    Type: (ISSN 0045-7949)
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Stability of time dependent and spatially varying flows; Proceedings of the Symposium, Hampton, VA, Aug. 19-23, 1985 (1987)
    In:  Other Sources
    Details
    Publication Date: 2016-03-09
    Description: Papers are presented on the application of stability theory to laminar flow control, secondary instabilities in boundary layers, a Floquet analysis of secondary instability in shear flows, and the generation of Tollmien-Schlichting waves by long wavelength free stream disturbances. Also considered are numerical experiments on boundary-layer receptivity, short-scale inviscid instabilities in the flow past surface-mounted obstacles, wave phenomena in a high Reynolds number compressible boundary layer, and instability of time-periodic flows. Other topics include high frequency Rayleigh instability of Stokes layers, stability and resonance in grooved-channel flows, finite length Taylor Couette flow, and vortical structures in the breakdown stage of transition.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Efficient solutions to the Euler equations for supersonic flow with embedded subsonic regions (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A line Gauss-Seidel (LGS) relaxation algorithm in conjunction with a one-parameter family of upwind discretizations of the Euler equations in two dimensions is described. Convergence of the basic algorithm to the steady state is quadratic for fully supersonic flows and is linear for other flows. This is in contrast to the block alternating direction implicit methods (either central or upwind differenced) and the upwind biased relaxation schemes, all of which converge linearly, independent of the flow regime. Moreover, the algorithm presented herein is easily coupled with methods to detect regions of subsonic flow embedded in supersonic flow. This allows marching by lines in the supersonic regions, converging each line quadratically, and iterating in the subsonic regions, and yields a very efficient iteration strategy. Numerical results are presented for two-dimensional supersonic and transonic flows containing oblique and normal shock waves which confirm the efficiency of the iteration strategy.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2523 , L-15975 , NAS 1.60:2523
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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