A semi-empirical theory is presented for the estimation of aerodynamic forces and moments acting on a steadily rotating (spinning) airplane fuselage, with a particular emphasis on the prediction of its auto-rotational behavior. This approach is based on an extension of the available analytical methods for high angle of attack and side-slip and then coupling this procedure with strip theory for application to a rotating airplane fuselage. The analysis is applied to the fuselage of a light general aviation airplane and the results are shown to be in fair agreement with experimental data.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    On the prediction of auto-rotational characteristics of light airplane fuselages


    Contributors:

    Publication date :

    1984-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






    Control of autorotational characteristics of light-airplane fuselages

    PAMADI, B. N. / JAMBUNATHAN, V. / RAHMAN, A. | AIAA | 1988


    Shaping of airplane fuselages for minimum drag

    DODBELE, S. / VAN DAM, C. / HOLMES, B. | AIAA | 1986


    Tests on airplane fuselages, floats and hulls

    Diehl, Walter S. | TIBKAT | 1925