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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Development of a computer program to obtain ordinates for NACA-6 and 6A-series airfoils


    Contributors:

    Publication date :

    1974-09-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :