A flight and wind tunnel investigation was conducted to determine the effects of Reynolds number on the installed boattail drag of an underwing nacelle. Tests were run on a modified F-106B aircraft and 0.05 and 0.22 scale wind tunnel models. Tests were conducted at Mach numbers of 0.6 and 0.9 and over a 16 to 1 range of Reynolds numbers. Highest drag was obtained at intermediate Reynolds numbers corresponding to about the lowest flight values and that of the 0.22 scale model. Significantly lower drag was obtained at both higher and lower Reynolds numbers.


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    Title :

    Flight and wind tunnel investigation of the effects of Reynolds number on installed boattail drag at subsonic speeds


    Contributors:

    Conference:

    Aerospace Sci. Meeting and Tech. Display ; 1973 ; Washington, D. C., United States


    Publication date :

    1972-01-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :