This study proposes a variable shock angle osculating flowfield waverider design method. The flow field structure and aerodynamic characteristics of osculating flowfield waveriders are also analyzed. In this method, the constraint of imposing the same conical flowfield on each osculating plane is removed because the shock angle of each osculating plane is different, which can be chosen according to the specific needs of waveriders. The obtained results show that the shock angle distribution is an important factor in the design of osculating flowfield waveriders. A waverider whose shock angle increases as a parabolic curve along the spanwise direction has a larger volume and lower lift-to-drag ratio. In contrast, a waverider whose shock angle decreases as a parabolic curve along the spanwise direction has a smaller volume and higher lift-to-drag ratio. Providing different shock angle distributions can lead to greater flexibility in the design and optimization of hypersonic waverider vehicles.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Novel Osculating Flowfield Methodology for Hypersonic Waverider Vehicles Based on Variable Shock Angle


    Beteiligte:
    Liu, Zhen (Autor:in) / Liu, Jun (Autor:in) / Ding, Feng (Autor:in) / Li, Kai (Autor:in) / Xia, Zhixun (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2018-05-10




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Unbekannt




    The Osculating Flowfield Method of Waverider Geometry Generation

    Rodi, P. E. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2005


    Preliminary Ramjet/Scramjet Integration with Vehicles Using Osculating Flowfield Waverider Forebodies

    Rodi, P. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012