On basis of certain simplifying structural and aerodynamic assumptions, notably that wing bending and torsion occur along straight line, and strip theory, differential equations of equilibrium of swept elastic wing subjected to aerodynamic and inertial loads are formulated; formulas for lift and moment coefficients in terms of initial configuration and elastic deflections of wing given.


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    Title :

    Formulation of aeroelastic problem for swept wing


    Additional title:

    J Aeronautical Sciences


    Contributors:
    Miles, J.W. (author)


    Publication date :

    1949


    Size :

    14 pages


    Remarks:

    Bibliography


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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