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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    Title :

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


    Contributors:
    W. S. Aiken (author)

    Publication date :

    1948


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English