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  • 1
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    AGARD standard aeroelastic configurations for dynamic response (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Since emphasis is on the transonic speed range, special importance is placed on configurations for which available data are sufficient to define accurately a transonic flutter boundary. Only configurations with clean, smooth surfaces are considered suitable. Segmented models or models with surface-slope discontinuities are inappropriate. Excluded also, in general, are configurations and data sets that involve behavior that is uncertain or not well understood, uncertain model properties, or know sensitivities to small variations in model properties. In order to assess the suitability of configurations already tested and the associated data for designation as standard, a survey of AGARD member countries was conducted to seek candidates for the prospective set. The results of that survey are given and summarized along with the initial selection of a standard configuration.
    Keywords: AERODYNAMICS
    Type: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1; p 243-259
    Format: application/pdf
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  • 2
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    Static aeroelastic effects on the flutter of a supercritical wing (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is well known that wings with supercritical airfoils generally have lower transonic flutter speeds than similar wings with conventional airfoils and that small increases in angle of attack from zero and the accompanying static aeroelastic deformations have further detrimental effects on transonic flutter. The results of an effort to calculate the effects of angle of attack and the associated aeroelastic deformation on the flutter of a highly swept supercritical wing (TF 8A) by use of the modified strip analysis employed in previous studies of this wing are presented. The spanwise distributions of steady-state section lift-curve slope and aerodynamic center required as input for these calculations were obtained from static aeroelastic calculations for the wing by use of the FL022 transonic code and an assumed dynamic pressure as that used to calculate the statically deformed shape and loading about which the flutter oscillation occurs. The results show that the unconventional backward turn of the transonic dip in the experimental flutter boundary for angles of attack greater than zero is caused by variations in mass ratio and not by static aeroelastic deformation, although inclusion of the latter appears to be required for quantitative accuracy in the calculations.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-89132 , NAS 1.15:89132
    Format: application/pdf
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  • 3
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    Development of computational methods for unsteady aerodynamics at the NASA Langley Research Center (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The current scope, recent progress, and plans for research and development of computational methods for unsteady aerodynamics at the NASA Langley Research Center are reviewed. Both integral-equations and finite-difference method for inviscid and viscous flows are discussed. Although the great bulk of the effort has focused on finite-difference solution of the transonic small-perturbation equation, the integral-equation program is given primary emphasis here because it is less well known.
    Keywords: AERODYNAMICS
    Type: NASA-TM-89133 , NAS 1.15:89133
    Format: application/pdf
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  • 4
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    Preliminary report on candidates for AGARD standard aeroelastic configurations for dynamic response (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the request of the Aeroelasticity Subcommittee of the AGARD Structures and Materials Panel, a survey of member countries has been conducted to seek candidates for a prospective set of standard configurations to be used for comparison of calculated and measured dynamic aeroelastic behavior with emphasis on the transonic speed range. This set is a sequel to that established several years ago for comparisons of calculated and measured aerodynamic pressures and forces. Approximately two dozen people in the United States, and more than three dozen people in the other member countries, were contacted. This preliminary report presents the results of the survey and an analysis of those results along with recommendations for the initial set of standard configurations and for additional experimental work needed to fill significant gaps in the available information.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-89142 , NAS 1.15:89142
    Format: application/pdf
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  • 5
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    Development of computational methods for unsteady aerodynamics at the NASA Langley Research Center (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The current scope, recent progress, and plans for research and development of computational methods for unsteady aerodynamics at the NASA Langley Research Center are reviewed. Both integral equations and finite difference methods for inviscid and viscous flows are discussed. Although the great bulk of the effort has focused on finite difference solution of the transonic small perturbation equation, the integral equation program is given primary emphasis here because it is less well known.
    Keywords: AERODYNAMICS
    Type: NAS 1.15:89133 , AGARD, Future Research on Transonic Unsteady Aerodynamics and Its Aeroelastic Applications; 20 p
    Format: text
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  • 6
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    On the permeability of porous materials (1956)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3596
    Format: application/pdf
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  • 7
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    Theoretical analysis of linked leading-edge and trailing-edge flap-type controls at supersonic speeds (1956)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3617
    Format: application/pdf
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  • 8
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    Calculation of flutter characteristics for finite-span swept or unswept wings at subsonic and supersonic speeds by a modified strip analysis (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-L57L10
    Format: application/pdf
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  • 9
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    Low-speed Wind-tunnel Investigation of Leading-edge Porous Suction on a 4-percent-thick 60 Degree Delta Wing (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-L54L21
    Format: application/pdf
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  • 10
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    AGARD standard aeroelastic configurations for dynamic response. Candidate configuration I.-wing 445.6 (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: To promote the evaluation of existing and emerging unsteady aerodynamic codes and methods for applying them to aeroelastic problems, especially for the transonic range, a limited number of aerodynamic configurations and experimental dynamic response data sets are to be designated by the AGARD Structures and Materials Panel as standards for comparison. This set is a sequel to that established several years ago for comparisons of calculated and measured aerodynamic pressures and forces. This report presents the information needed to perform flutter calculations for the first candidate standard configuration for dynamic response along with the related experimental flutter data.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-100492 , NAS 1.15:100492
    Format: application/pdf
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