Compression shocks which lead from supersonic to subsonic velocity causeflow to separate on impact on rigid wall; such shocks appear at bodies with circular symmetry of wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high back pressure; form of compression shocks observed therein is investigated. English translation from (ZWB) Deutsche Luftfahrtforschung, Forschungsbericht n 1850, Aug 12 1943.


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    Title :

    Compression shocks of detached flow


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Memo


    Contributors:
    Eggink (author)


    Publication date :

    1947


    Size :

    15 pages


    Remarks:

    10 Supp Sheets


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :