A concept to obtain shock free transonic flows for design aerodynamics of aircraft and turbomachinery is outlined. The method of elliptic continuation or method of fictitious gas represents a starting point for a number of operational computational procedures to obtain supercritical airfoil and wings. Design examples illustrate the value of shock free configuration for aerodynamic efficiency enhancement. The application of supercritical flow in aerodynamic concepts is mentioned.


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    Title :

    Aerodynamic Design Methods for Modern Transport Aircraft


    Contributors:

    Publication date :

    1985


    Size :

    82 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English