Loads were measured at altitudes to 35,000 ft and Mach numbers to 0.82; data from rudder step, aileron-roll, and steady sideslip maneuvers were reduced to give derivatives of horizontal tail normal force and rolling moment coefficients with respect to sideslip angle and rate of change of wing fuselage combination pitching moment coefficient with sideslip angle.


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    Title :

    Analysis of incremental horizontal-tail loads measured on swept-wing bomber airplane in sideslip maneuvers


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1959


    Size :

    34 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :