An airfoil designed for helicopter rotor application is investigated. The airfoil is designed to increase maximum normal force coefficient while maintaining favorable drag divergence and pitching moment characteristics. Two modifications are also tested. Maximum normal force coefficient varies from 1.14 to 0.90 at Mach numbers from about 0.35 to 0.65. Both modifications decreased drag coefficient at zero normal force coefficient for Mach numbers near drag divergence, but were less beneficial at a normal force coefficient of -0.2.


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    Title :

    Two-dimensional aerodynamic characteristics of an airfoil designed for two


    Contributors:

    Publication date :

    1981-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :



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