The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases.


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    Titel :

    3D numerical simulation of clamshell thrust reverser with flap deployed while landing


    Beteiligte:
    Liu, Chunyang (Autor:in) / Wang, Zhanxue (Autor:in) / Wang, Jiaqi (Autor:in) / Yin, Fang (Autor:in) / Kong Deying, (Autor:in)


    Erscheinungsdatum :

    01.06.2010


    Format / Umfang :

    755489 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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