The design of shockless airfoils that are appropriate for experimental work on a supersonic transport with an oblique wing are examined. A series of computer codes for the design and analysis of airfoils and wings in two dimensional and three dimensional transonic flow are studied. The oblique wing 3-D code was the forerunner of the later swept wing code. Techniques to incorporate the effect of an engine or fuselage in the inverse design code while using a minimum of computer resources are developed.


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    Title :

    Study of Transonic Flow over Swept Wings


    Publication date :

    1983


    Size :

    3 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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