A flight investigation was conducted to determine the contributions of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The tests covered a Mach number range from 0.2 to 0.8. The loads on the various airplane components were measured by the use of calibrated strain-gage installations located at the roots of the wings and horizontal tail surfaces.


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    Titel :

    Flight Determination of Wing and Tail Loads on a Fighter-Type Airplane by Means of Strain-Gage Measurements


    Beteiligte:
    W. S. Aiken (Autor:in)

    Erscheinungsdatum :

    1948


    Format / Umfang :

    24 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch