The results of a comprehensive theoretical and experimental investigation of the flow pattern of V-shaped wings at supersonic flow velocities are presented. Applicability of the previously established criteria for the existence of nonviscid vortex structures in cases of formation of a contact discontinuity of a corresponding intensity, originating from the point of separation of the λ-configuration of shock waves, accompanying separation of the turbulent boundary layer, influenced by the internal compression shock incident on one of the wing panel, is shown. A wide variety of flow patterns in the shock layer near the wing with an opening angle γ > π depending on the Mach number, angles of attack and slip, which had not been previously described, was found. They, in particular, include: flow separation from the leeward console and presence of a vortex in the flow modes with a slip; flow transition on a sphere in the vicinity of the central chord of the wing from subsonic to trans- and supersonic one both along the contour of the vortex and in the return flow in a vortex near the wall of the lee console with the shock waves formation. An experimental investigation of the flow patterns with a vortex downstream the salient point of the outline qualitatively confirmed the calculation results on the flow structure outside the vortex. A separation of the turbulent boundary layer is revealed in the return flow within the vortex, due to the counter pressure gradient.


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    Title :

    V-shaped wings in supersonic flow


    Contributors:
    Maksimov, FA (author) / Ostapenko, NA (author) / Zubin, MA (author)


    Publication date :

    2022-03-01


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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