Linearized equations of motion of rolling bisymmetric aircraft formulated, using body axes; it is shown that (a) rate of change of angle of attack is vector, (b) linearized form of downwash lag terms is valid only if downwash-roll angle be small, and (c) such linearized form must use vector relations of (a); as result, stability criteria are derived independent of rolling of reference axis system.


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    Title :

    Response of bisymmetric aircraft to small combined pitch, yaw, and roll control actions


    Additional title:

    J Aeronautical Sciences


    Contributors:
    Davis, R.A. (author)

    Published in:

    Publication date :

    1957


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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