A static aeroelastic analysis is presented of the divergence of untapered wings with conventional and supercritical airfoil sections at sweep angles of zero and -15 deg. One bending and one torsion mode were employed for a uniform rectangular cantilevered beam with the elastic axis at midchord, and calculations were based on a two-dimensional differential equations formulation in the structural coordinate system and in simple strip theory. A minimum divergence speed in the transonic range is obtained which is associated with the rearward shift of the aerodynamic center, and a 17% difference in minimum divergence dynamic pressure is found between a supercritical and a conventional wing. It is noted that although the strip method employed allows the assessment of the sensitivity of airfoil shapes to divergence, three-dimensional transonic aerodynamic methods should be used to predict wing divergence characteristics.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Illustration of airfoil shape effect on forward-swept wing divergence


    Contributors:

    Published in:

    Publication date :

    1980-10-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English