Transonic steady and unsteady pressure tests have been conducted in the Langley transonic dynamics tunnel on a large elastic wing known as the DAST ARW-2. The wing has a supercritical airfoil, an aspect ratio of 10.3, a leading-edge sweep back angle of 28.8 degrees, and two inboard and one outboard trailing-edge control surfaces. Only the outboard control surface was deflected to generate steady and unsteady flow over the wing during this study. Only the steady surface pressure, control-surface hinge moment, wing-tip deflection, and wing-root bending moment measurements are presented. The results from this elastic wing test are in tabulated form to assist in calibrating advanced computational fluid dynamics (CFD) algorithms.


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    Titel :

    Steady pressure measurements on an Aeroelastic Research Wing (ARW-2)


    Beteiligte:

    Erscheinungsdatum :

    1994-02-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Steady Pressure Measurements on an Aeroelastic Research Wing (ARW-2)

    M. C. Sandford / D. A. Seidel / C. V. Eckstrom | NTIS | 1994


    Unsteady-Pressure and Dynamic-Deflection Measurements on an Aeroelastic Supercritical Wing

    Seidel, David A. / Sandford, Maynard C. / Eckstrom, Clinton V. | NTRS | 1991