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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    Titel :

    Study of Transonic Flow over Swept Wings


    Erscheinungsdatum :

    1983


    Format / Umfang :

    3 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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