The pressure distribution over thin oblique airfoils at subsonic speeds is studied. It is found that the flows again can be obtained by the superposition of elementary conical flow fields. In the case of the sweptback wing the pressure distributions remain qualitatively similar at subsonic and supersonic speeds. Thus a distribution similar to the Ackeret type of distribution appears on the root sections of the sweptback wing at M = 0. The resulting positive pressure drag on the root section is balanced by negative drags on outboard sections.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Subsonic flow over thin oblique airfoils at zero lift


    Beteiligte:
    Jones, R. T. (Autor:in)


    Erscheinungsdatum :

    01.02.1976


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :





    Subsonic flow over thin oblique airfoils at zero lift

    Jones, R.T. | Engineering Index Backfile | 1947


    Subsonic flow over thin oblique airfoils at zero lift

    Jones, R.T. | Engineering Index Backfile | 1948