An experimental study and an analytical study have been conducted to examine static divergence for hypersonic-vehicle wing models at supersonic conditions. A supersonic test in the Langley Unitary Plan Wind Tunnel facility was conducted for two wind-tunnel models. These models were nearly identical with the exception of airfoil shape. One model had a four-percent maximum thickness airfoil and the other model had an eight-percent maximum thickness airfoil. The wing models had low-aspect ratios and highly swept leading edges. The all-movable wing models were supported by a single-pivot mechanism along the wing root. For both of the wind-tunnel models, configuration changes could be made in the wing-pivot location along the wing root and in the wing-pivot pitch stiffness. Three divergence conditions were measured for the four-percent thick airfoil model in the Mach number range of 2.6 to 3.6 and one divergence condition was measured for the eight-percent thick airfoil model at a Mach number of 2.9. Analytical divergence calculations were made for comparison with experimental results and to evaluate the parametric effects of wing-pivot stiffness, wing-pivot location, and airfoil thickness variations. These analyses showed 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 predicted the trend of experimental divergence dynamic pressure with Mach number accurately; however, the calculations were approximately 25 percent conservative with respect to dynamic pressure.


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    Title :

    Supersonic aeroelastic instability results for a NASP-like wing model


    Additional title:

    Die aeroelastische Instabilität im Überschallbereich an einem Tragflächenmodell eines nationalen Raumflugzeuges


    Contributors:
    Cole, S.R. (author) / Florance, J.R. (author) / Thomason, L.B. (author) / Spain, C.V. (author) / Bullock, E.P. (author)


    Publication date :

    1993


    Size :

    10 Seiten, 16 Bilder, 2 Tabellen, 15 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    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


    Supersonic aeroelastic instability results for a NASP-like wing model

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