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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    Title :

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


    Contributors:
    G. Ehn (author)

    Publication date :

    1974


    Size :

    112 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English