Numerical results are presented from a reacting-flow Navier-Stokes simulation of a rocket nozzle in which fuel is injected downstream of the nozzle throat for the purposes of augmenting the thrust. The numerical results are compared with experimental data in terms of overall thrust and specific impulse as well as pressure distribution along the nozzle wall. The flow physics associated with the thrust augmentation is also described. The investigation shows that propellant injection downstream of the throat is a viable method for augmenting rocket thrust. In addition, the augmented thrust levels increase with increasing levels of injected mass flow. Finally, the investigation shows that the numerical predictions are in good agreement with the experimental results.


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    Title :

    Numerical Simulation of a Thrust Augmented Rocket Nozzle


    Contributors:
    R. L. Davis (author) / M. J. Bulman (author) / C. Yam (author)

    Publication date :

    2006


    Size :

    11 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Numerical Simulation of a Thrust Augmented Rocket Nozzle

    Davis, Roger / Bulman, Melvin / Yam, Clement | AIAA | 2006


    Numerical Simulation of a Thrust Augmented Rocket Nozzle

    Davis, R. / Bulman, M. / Yam, C. et al. | British Library Conference Proceedings | 2006