Method for predicting nozzle performance of microthrust rockets is discussed. Method is numerical and uses simplified computer program on IBM 360/65 computer. Analysis is based on slender channel equations with slip boundary conditions at walls. Implicit finite difference scheme is used to calculate pressure and velocity profiles along channel.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Final report on a study of low-density nozzle flows, with application to microthrust rockets


    Publication date :

    1972-12-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :