A computational method for the steady 2-D flow in axially symmetrical rocket nozzles with a given profile is developed, in order to determine the Maximum thrust contour of rocket engine nozzles with large expansion ratio. The optimized nozzles proved a more than 10% increase in the integral specific impulse recorded during the variable altitude atmospheric flight of rocket vehicles. The method is well suited for application in the design of the optimum contour for axially-symmetric nozzles for atmospheric rocket ascent, specifically for aerospike type nozzles, as for other similar industrial applications in gas and steam turbine technology.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Inviscid Nozzle for Aerospike Rocket Engine Application



    Published in:

    Publication date :

    2015-11-26


    Size :

    5 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle

    Stewart, Kyle J. / Papadopoulos, Periklis / Pollard, Jordan | AIAA | 2020


    Optimized Dual-Expander Aerospike Nozzle Upper Stage Rocket Engine

    Hall, Joshua / Hartsfield, Carl / Simmons, Joseph et al. | AIAA | 2011


    NUCLEAR THERMAL ROCKET ENGINE WITH A TOROIDAL AEROSPIKE NOZZLE

    Stewart, Kyle J. / Papadopoulos, Periklis / Pollard, Jordan | TIBKAT | 2020