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:
    Stark, R. (author) / Génin, C. (author)

    Published in:

    Publication date :

    2016-06-30


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    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