A computer program was developed to produce the ordinates for airfoils of any thickness, thickness distribution, or camber in the NACA 6- and 6A-series. For the 6-series and for all but the leading edge of the 6A-series, agreement between the ordinates obtained from the new program and previously published values is generally within .00005 chord. Near the leading edge of the 6A-series airfoils, differences up to .00035 chord are found. (Author)


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    Title :

    Development of a Computer Program to Obtain Ordinates for Naca-6 and 6A-Series Airfoils


    Contributors:
    C. L. Ladson (author) / C. W. Brooks (author)

    Publication date :

    1974


    Size :

    103 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English