A possible reason is suggested for the induced rolling moments occurring on wraparound-fin configurations in subsonic flight at zero angle of attack. The subsonic potential flow over the configuration at zero incidence is solved numerically. The body is simulated by a distribution of sources along its axis, and the fins are described by a vortex-lattice method. It is shown that rolling moments can be induced on the antisymmetric fins by the radial flow generated at the base of the configuration, either over the converging separated wake, or over the diverging plume of rocket motor.


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    Title :

    The evaluation of the rolling moments induced by wraparound fins


    Contributors:
    Seginer, A. (author) / Bar-Haim, B. (author)

    Publication date :

    1983-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







    Aerodynamics of wraparound fins

    Seginer, A. / Bar-Haim, B. | NTRS | 1983


    Aerodynamics of wraparound fins

    SEGINER, A. / TechnionIsrael Institute of Technology / Haifa et al. | AIAA | 1983