Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.


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    Title :

    Preliminary Wind-tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92


    Contributors:

    Publication date :

    1956-06-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English