The locally linearized longitudinal and lateral-directional aerodynamic stability and control derivatives for the X-29A aircraft were calculated for altitudes ranging from sea level to 50,000 ft, Mach numbers from 0.2 to 1.5, and angles of attack from -5 deg to 25 deg. Several other parameters were also calculated, including aerodynamic force and moment coefficients, control face position, normal acceleration, static margin, and reference angle of attack.


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    Title :

    Locally linearized longitudinal and lateral-directional aerodynamic stability and control derivaties for the X-29A aircraft


    Contributors:
    Budd, G. D. (author)

    Publication date :

    1984-01-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :