Abstract An inverse nozzle design method based on maximum thrust theory and method of characteristics (MOC) is proposed to increase the aerodynamic performance and practicality of scramjet nozzles. In comparison with the general maximum thrust nozzle design method, the proposed method not only utilizes maximum thrust theory but also demonstrates additional flexibility under geometrical constraints. The main characteristic of the proposed method is that the key point in the maximum thrust nozzle can become the target and be manually determined in advance in accordance with the actual requirements, rather than through an iteration method based on the flow conditions of the nozzle inlet and flight in the general design method. The proposed method is implemented using MOC, which is a universal mathematical method in solving partial differential equations. First, a brief introduction of maximum thrust theory and MOC are provided to comprehend the background. Second, the application of maximum thrust theory in the inverse design method is discussed, including the specific design procedure. Third, the feasibility and effectiveness of the proposed method are verified in an actual design case using computational fluid dynamic approaches. Then, the influence of cowl lengths on the aerodynamic performance of the nozzle is analyzed. Results show that the proposed method can provide different solutions to obtain high thrust coefficient or high lift and pitching moments, which offers flexibility and operability for the engineers. Finally, a nozzle named nozzle B is designed using the traditional forward method. In terms of aerodynamic performance, the nozzle A designed by the proposed method shows evident advantages. The thrust coefficient of nozzle A obtains approximately 31.8% increment, and the lift and pitching moments improve with 201.0% and 56.6% increments, respectively. In conclusion, this study proposes a new inverse nozzle design method that utilizes maximum thrust theory and MOC, which can not only increase the aerodynamic performance but also provide further flexibility and operability in the scramjet nozzle design.

    Highlights A design method of scramjet nozzles is proposed on the basis of MOC. The proposed design method adopts maximum thrust theory. The proposed method is verified by CFD tool. The proposed method can increase the aerodynamic performance of the nozzle. The nozzle cowl can be determined according to the actual performance requirement.


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    Titel :

    Inverse design method on scramjet nozzles based on maximum thrust theory


    Beteiligte:
    Yu, Kaikai (Autor:in) / Chen, Yile (Autor:in) / Huang, Shuai (Autor:in) / Xu, Jinglei (Autor:in)

    Erschienen in:

    Acta Astronautica ; 166 ; 162-171


    Erscheinungsdatum :

    2019-10-09


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Maximum Thrust Nozzles

    WILLIAM E . CONWAY AND AARS CELMINS | AIAA | 1972


    Design of Shrouded-Plug Nozzles for Maximum Thrust

    RICHARD VANDER VEEN AND ROY GENTRY AND JOE D. HOFFMAN | AIAA | 1974



    Off-Design Performance of Scramjet Nozzles

    Hiraiwa, T. / Ueda, S. / Sato, S. et al. | British Library Conference Proceedings | 1993


    Design of shronded-plug nozzles for maximum thrust

    Van der Veen, R. / Gentry, R. / Hoffman, J. | Tema Archiv | 1974