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  • 1
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    Adaptation of a four-wall interference assessment/correction procedure for airfoil tests in the 0.3-m TCT (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Based upon limited, initial observations of wall interference corrections obtained for one airfoil test, there is a need for assessing the upstream flow direction. If there is no direct measurement then a two-pass correction procedure similar to the one described here is required. Questions have arisen pertaining to the correct interpretation of the pressure coefficients measured on the slats of a slotted tunnel wall, the interpretation of just what the calculated equivalent body encompasses or should include, and what can or should be considered as quantitative criteria for data correctability. Further studies using this modified procedure will address these questions. Hopefully, a meaningful WIAC procedure can be validated for the airfoil tests in the 0.3-m TCT.
    Keywords: AERODYNAMICS
    Type: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 393-414
    Format: text
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  • 2
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    An inerference assessment approach for a three-dimensional slotted tunnel with sparse wall pressure data (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The various procedures referred to as wall interference assessment and correction procedures presume the existence of a surface distribution of data (usually static pressure) measured over a surface on or near the tunnel walls for each test point to be assessed. An alternative approach in which a reasonably sophisticated computer model of the test section flow would be fitted parametrically to a sparse set of measured data is presented. The measurements provides line distributions of static pressure near the center lines of the top, side and bottom walls. The development of a test section model incorporating explicit recognition of discrete slots of finite length with controlled flow reentry into the solid wall downstream portion of the tunnel is shown.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 323-334
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  • 3
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    Wall interference effects: Status review (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The interference technology incorporated into the NTF design (hardware) and the emerging transonic wall interference assessment correction procedures (software) to be employed when the NTF becomes operational was reviewed. It is anticipated that the early experiments will provide data relevant to wall interference effects.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 123-241
    Format: text
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  • 4
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    Wall interference assessment and corrections (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Wind tunnel wall interference assessment and correction (WIAC) concepts, applications, and typical results are discussed in terms of several nonlinear transonic codes and one panel method code developed for and being implemented at NASA-Langley. Contrasts between 2-D and 3-D transonic testing factors which affect WIAC procedures are illustrated using airfoil data from the 0.3 m Transonic Cryogenic Tunnel and Pathfinder 1 data from the National Transonic Facility. Initial results from the 3-D WIAC codes are encouraging; research on and implementation of WIAC concepts continue.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 817-851
    Format: application/pdf
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  • 5
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    Hypersonic viscous interaction on sharp and blunt inclined plates. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mach 42 test measuring surface pressures, surface heat transfer rates and shock wave shapes in strong interaction regime for sharp and blunt plates
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 68-720 , ; ADEMIE DES SCIENCES|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, FLUID AND PLASMA DYNAMICS CONFERENCE; Jun 24, 1968 - Jun 26, 1968; LOS ANGELES, CALIF.
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  • 6
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    A vector-continuous loading concept for aerodynamic panel methods (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approach to the reduction of discretization errors in aerodynamic panel methods is presented. The approach is based on preventing the occurence of induced velocity singularities at panel slope discontinuities by maintaining continuity of the velocity jump vector across the panels. The approach was implemented in a two-dimensional incompressible panel method formulation and evaluated by application to several external and internal flow problems. The method is shown to exhibit a second order accuracy trend and to produce smaller errors with velocity component boundary conditions imposed on the real flow than with equipotential boundary conditions imposed on the imaginary flow behind the panels. For flows around airfoil sections with either sharp or blunt trailing edges, the method gives excellent agreement with results from a well developed finite difference method. The method is well behaved and is insensitive to irregularities in panel size distribution.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80104
    Format: application/pdf
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  • 7
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    Wind-tunnel tests of a 1/4 scale model of the Bell XS-1 transonic airplane. 1: Longitudinal stability and control characteristics (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 1/4 scale model of the Bell XS-1 transonic aircraft was tested in the Langley 300 mile-per-hour 7 by 10 foot tunnel to determine its low speed longitudinal stability and control characteristics. Pertinent longitudinal flying qualities expected of the XS-1 research airplane were estimated from the results of these tests including the effects of compressibility likely to be encountered at speeds below the force break. It appears that the static longitudinal stability and elevator control power will be adequate, but that the elevator control force gradient in steady flight will be undesirably low for all configurations. It is suggested that a centering spring be incorporated in the elevator control system of the airplane in order to increase the control force gradient in steady flight and in maneuvers.
    Keywords: AERODYNAMICS
    Type: L6D12 , Collected Works of Charles J. Donlan; 78 p
    Format: text
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  • 8
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    Hypersonic viscous interaction on sharp and blunt inclined plates. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mach 42 test measuring surface pressures, surface heat transfer rates and shock wave shapes in strong interaction regime for sharp and blunt plates
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 68-720 , FLUID AND PLASMA DYNAMICS CONFERENCE; Jun 24, 1968 - Jun 26, 1968; LOS ANGELES, CA
    Format: text
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