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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    Title :

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


    Contributors:

    Publication date :

    1994


    Size :

    537 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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

    Sandford, Maynard C. / Seidel, David A. / Eckstrom, Clinton V. | NTRS | 1994


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

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