Wind tunnel measurements of an ogive delta wing model with 64.4 deg leading edge sweepback were carried out in a supersonic transonic l sq meter wind tunnel. Static and dynamic tests were carried out over a range of mach numbers from low transonic speed up to M l.92, 3- 5-, and 6-component strain gauge balance measurements and flow visualization tests were also performed. The angle of attack range includes angles at which vortex breakdown occurs.


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    Titel :

    Measurements of Static Stability Coefficients of an Ogive delta Wing Model at Transonic and Supersonic Speeds


    Beteiligte:
    G. Ehn (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    112 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch