Supersonic rocket-powered, winged, and wingless models were tested to Mach 1.4 to determine effect of nose fineness ratio on total and component drag. Winged models with and without sweepback were tested. Results show that increased nose fineness ratio increased wing-body drag near Mach 1.0 but decreased total drag at higher Mach. Increased fineness ratio decreased drag of wingless bodies. Wing drag values change with installation on different body shapes.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Results of Flight Tests at Supersonic Speeds to Determine the Effect of Body Nose Fineness Ratio on Body and Wing Drag


    Contributors:
    E. R. Katz (author)

    Publication date :

    1947


    Size :

    26 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English