During transient start-up and shutdown of rocket engines under sea-level conditions, the flow inside the supersonic part of the nozzle separates from the wall. The separated flow is asymmetrically distributed around the circumference and hence induces side loads. A cold flow subscale test campaign was carried out at DLR to study a device that reduces the side loads of a thrust-optimized parabolic nozzle under transient conditions. A detailed parametrical study was performed. The experimental data demonstrated and quantified the side load reduction potential of the device.


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    Title :

    Optimization of a Rocket Nozzle Side Load Reduction Device


    Contributors:

    Published in:

    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040





    Optimisation of a Rocket Nozzle Side Load Reduction Device

    Stark, Ralf / Genin, Chloe | AIAA | 2012


    Experimental Study on Rocket Nozzle Side Load Reduction

    Stark, Ralf / Génin, Chloé | AIAA | 2011


    EXPERIMENTAL STUDY ON ROCKET NOZZLE SIDE LOAD REDUCTION

    Stark, R. / Genin, C. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2011