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  • 1
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    Flow computations for the Space Shuttle in ascent mode using thin-layer Navier-Stokes equations (1990)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-19
    Beschreibung: The application of CFD techniques to the Space Shuttle ascent environment was aggressively undertaken in the wake of the Challenger accident in order to secure a major new source of aerodynamic information for both the nominal and mission-abort conditions, using Cray 2 and Cray YMP supercomputers. Due to the integrated vehicle's complexity, the 'chimera' composite grid approach, in which an overset body-conforming grid is used to represent each geometric component as well as special flow regions, was employed for the discretization process. Calculation results exhibit general agreement in both flow structure and surface pressure with the available wind tunnel and flight-test results.
    Schlagwort(e): AERODYNAMICS
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Implementation of wall boundary conditions for transpiration in F3D thin-layer Navier-Stokes code (1991)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-27
    Beschreibung: Numerical boundary conditions for mass injection/suction at the wall are incorporated in the thin-layer Navier-Stokes code, F3D. The accuracy of the boundary conditions and the code is assessed by a detailed comparison of the predictions of velocity distributions and skin-friction coefficients with exact similarity solutions for laminar flow over a flat plate with variable blowing/suction, and measurements for turbulent flow past a flat plate with uniform blowing. In laminar flow, F3D predictions for friction coefficient compare well with exact similarity solution with and without suction, but produces large errors at moderate-to-large values of blowing. A slight Mach number dependence of skin-friction coefficient due to blowing in turbulent flow is computed by F3D code. Predicted surface pressures for turbulent flow past an airfoil with mass injection are in qualitative agreement with measurements for a flat plate.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 91-3204 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Transonic wind tunnel wall interference analysis for the Space Shuttle Launch Vehicle (1993)
    In:  Other Sources
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    Publikationsdatum: 2019-07-13
    Beschreibung: The AEDC perforated-wall boundary condition has been incorporated into the NASA Ames OVERFLOW code and has been used to calculate the tunnel flow field in the AEDC Aerodynamic Wind Tunnel (16T) over a three-percent model of the Space Shuttle Launch Vehicle. Tunnel flow-field calculations have been performed for two supersonic flow-field conditions, including one near sonic condition. Wall interference assessments and analyses have been performed by making detailed comparisons of the tunnel flow-field calculations with corresponding free-air flow-field calculations and with tunnel data from different scale models. A capability to assess wall interference at low supersonic conditions and to improve data correlations with CFD results by adding the tunnel wall boundary condition is demonstrated.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 93-0420 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 17 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Structural dynamic and aeroelastic considerations for hypersonic vehicles (1991)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The specific geometrical, structural, and operational environment characteristics of hypersonic vehicles are discussed with particular reference to aerospace plane type configurations. A discussion of the structural dynamic and aeroelastic phenomena that must be addressed for this class of vehicles is presented. These phenomena are in the aeroservothermoelasticity technical area. Some illustrative examples of recent experimental and analytical work are given. Some examples of current research are pointed out.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-104110 , NAS 1.15:104110 , AIAA/ASME/ASCE/AHS/ASC 32d Structures, Structural Dynamics, and Materials Conference; Apr 08, 1991 - Apr 10, 1991; Baltimore, MD; United States
    Format: application/pdf
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  • 5
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    Numerical dissipation in F3D thin-layer Navier-Stokes solution for flows with wall transpiration (1992)
    In:  Other Sources
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    Publikationsdatum: 2019-07-12
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 5; p. 678-684.
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental transonic flutter characteristics of supersonic cruise configurations (1990)
    In:  Other Sources
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    Publikationsdatum: 2019-07-13
    Beschreibung: The flutter characteristics of a generic arrow-wing supersonic transport configuration are studied. The wing configuration has a 3 percent biconvex airfoil and a leading-edge sweep of 73 deg out to a cranked tip with a 60 deg leading-edge sweep. The ground vibration tests and flutter test procedure are described. The effects of flutter on engine nacelles, fuel loading, wing-mounted vertical fin, wing angle-of-attack, and wing tip mass and stiffness distributions are analyzed. The data reveal that engine nacelles reduce the transonic flutter dynamic pressure by 25-30 percent; fuel loadings decrease dynamic pressures by 25 percent; 4-6 deg wing angles-of-attack cause steep transonic boundaries; and 5-10 percent changes in flutter dynamic pressures are the result of the wing-mounted vertical fin and wing-tip mass and stiffness distributions.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 90-0979 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Apr 02, 1990 - Apr 04, 1990; Long Beach, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    The Baldwin-Lomax model for separated and wake flows using the entropy envelope concept (1992)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: Implementation of the Baldwin-Lomax algebraic turbulence model is difficult and ambiguous within flows characterized by strong viscous-inviscid interactions and flow separations. A new method of implementation is proposed which uses an entropy envelope concept and is demonstrated to ensure the proper evaluation of modeling parameters. The method is simple, computationally fast, and applicable to both wake and boundary layer flows. The method is general, making it applicable to any turbulence model which requires the automated determination of the proper maxima of a vorticity-based function. The new method is evalulated within two test cases involving strong viscous-inviscid interaction.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 92-0148
    Format: text
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    NASA TECHNICAL REPORTS
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