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 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.
V-shaped wings in supersonic flow
2022-03-01
11 pages
Article (Journal)
Electronic Resource
English
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