Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.


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    Title :

    The calculation of span LCAD distributions of swept-back wings


    Contributors:

    Publication date :

    1941-12-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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