A circular-arc - conic boattail nozzle, typical of those used on a twin engine fighter, was tested on an underwing nacelle mounted on an F-106B aircraft. The boattail had a radius ratio r/r sub c of 0.41 and a terminal boattail angle of approximately 19 deg. The gas generator was a J85-GE-13 turbojet engine. The effects of Reynolds number and angle of attack on boattail pressure drag and boattail pressure profiles were investigated. Increasing Reynolds number resulted in reduced boattail drag at both Mach numbers of 0.6 and 0.9. (Author)


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    Title :

    Flight Reynolds Number Effects on a Fighter-Type, Circular-Arc-19 Deg Conic Boattail Nozzle at Subsonic Speeds


    Contributors:

    Publication date :

    1974


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English