Buffeting tests were made on an aeroelastic model of a slender wing aircraft at Mach numbers of 0.2 and 0.3 and at low densities, over an angle of incidence range from 0 to 24 deg. In general the wing-root strains resembled those measured previously on an ordinary wind-tunnel model with almost the same shape. The total damping in the first and third symmetric modes was derived from tape records of the wing-root strain signal. For both modes the total damping was almost independent of the angle of incidence, even in the region of vortex breakdown. For the first mode the measured aerodynamic damping was reasonably predicted by assuming that the model was a slender delta wing with attached flow. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Some Measurements of Buffeting on an Aeroelastic Model of a Slender Wing Aircraft


    Contributors:
    D. G. Mabey (author) / C. W. Skingle (author) / J. C. Copley (author)

    Publication date :

    1978


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Some static aeroelastic considerations of slender aircraft

    Hancock, G.J. | Engineering Index Backfile | 1961


    Aeroelastic analysis of a slender wing

    Malik, Sheharyar / Ricci, Sergio / Riccobene, Luca | Springer Verlag | 2020