The theory (wing experiments in an artificial air stream are subject to error, due to the fact that the wing is not situated in an unlimited body of air) by means of which the given drag correction was obtained, was based on various assumptions (e.g., elliptical distribution of lift) which do not always hold true. For this reason it was desirable to test the equation for the additional drag in regard to its reliability and range of application.


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    Title :

    Wind tunnel tests of correction formula for wings of large span


    Contributors:

    Publication date :

    1924-05-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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