The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated.


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    Title :

    Pressure-Distribution Measurements on a Straight and on a 35 Degree Swept-Back Tapered Wing


    Contributors:
    Thiel, A. (author) / Weissinger, J. (author)


    Publication date :

    1947-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :