Two wing-alone wind-tunnel models were tested in the NASA Langley Unitary Plan Wind Tunnel facility to study the static divergence behavior of such configurations and to provide a data base for correlation with supersonic analytical predictions. One model had a four percent maximum thickness airfoil and the other had an eight-percent maximum thickness airfoil. The wing models had low aspect ratios and highly swept leading edges. Results show that decreasing airfoil thickness, moving the wing-pivot location upstream, or increasing the pitch-pivot stiffness have the beneficial effect of increasing the divergence dynamic pressures. The calculations accurately predicted the trend of experimental divergence dynamic pressure with Mach number.


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    Titel :

    Supersonic aeroelastic instability results for a NASP-like wing model


    Beteiligte:


    Erscheinungsdatum :

    1993-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Supersonic aeroelastic instability results for a NASP-like wing model

    Cole, S.R. / Florance, J.R. / Thomason, L.B. et al. | Tema Archiv | 1993


    Supersonic Aeroelastic Instability Results for a Nasp-Like Wing Model

    S. R. Cole / J. R. Florance / L. B. Thomason et al. | NTIS | 1993


    Supersonic aeroelastic instability results for a NASP-like wing model

    Cole, Stanley R. / Florance, James R. / Thomason, Lee B. et al. | NTRS | 1993


    SUPERSONIC AEROELASTIC INSTABILITY RESULTS FOR A NASP-LIKE WING MODEL

    COLE, STANLEY / FLORANCE, JAMES / THOMASON, LEE et al. | AIAA | 1993