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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    A transonic-small-disturbance wing design methodology


    Contributors:

    Publication date :

    1988-03-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :