Tests to determine aerodynamic characteristics of semi-span tail surface of fighter type airplane were carried to maximum Mach number of 0.7 except for model configurations for which maximum allowable loads were reached at lower speeds; results show effects of elevator nose shape, elevator trailing edge angle, and trailing edge strips.


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    Title :

    Tests of full-scale horizontal tail surface in Langley 16-foot high-speed tunnel


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1946


    Size :

    24 pages


    Remarks:

    Supp sheets, Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English