An automated transonic design code has been developed which modifies an initial airfoil or wing in order to generate a specified pressure distribution. The design method uses an iterative approach that alternates between a potential-flow analysis and a design algorithm that relates changes in surface pressure to changes in geometry. The analysis code solves an extended small-disturbance potential-flow equation and can model a fuselage, pylons, nacelles, and a winglet in addition to the wing. A two-dimensional option is available for airfoil analysis and design. Several two- and three-dimensional test cases illustrate the capabilities of the design code.


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    Title :

    Transonic-Small-Disturbance Wing Design Methodology


    Contributors:

    Publication date :

    1988


    Size :

    32 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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