When velocity of flight approaches that of sound, considerable increase of drag occurs due to boundary layer separation caused by shock waves; experiments showed that drag increase may be considerably reduced by suction of boundary layer. English translation from ZWB Forschungsbericht n 1424 July 1 1941.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Drag reduction by suction of boundary layer separated behind shock wave formation at high Mach numbers


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Memo


    Contributors:


    Publication date :

    1947


    Size :

    13 pages


    Remarks:

    5 Supp Sheets


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :