An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Free-flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-span Ailerons


    Contributors:

    Publication date :

    1948-10-25


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English