| Abstract: | The shock wave structure of flow around a V-wing and its properties determining the conical flow topology are numerically
investigated within the framework of the inviscid gas model on a wide range of the angles of attack and yaw when in the disturbed
supersonic flow either nonsymmetric Mach interaction between the shocks attached to the leading edges of the wing or a shockless
flow in the compressed layer on the windward cantilever is realized. The subranges of the angles of attack and yaw with the
disturbed flow properties characteristic of the wing of the given geometry are determined. It is found that at high angles
of attack, when the branching point of the bow shock beneath the leeward cantilever generates an intense contact discontinuity,
the structure of the conical flow in the shock layer on the windward cantilever involves a singularity of a new type which
can be characterized as a “vortical” Ferri singularity. It is located above the point of convergence of the streamlines proceeding
from the leading edges of the wing, at the vertex of the corresponding contact discontinuity. Flow patterns with the point
of convergence of the streamlines proceeding from the leading edges located in the elliptical flow region, which is placed
at a local maximum of the pressure distribution over the surface are also found. The range of the angles of attack and yaw
on which this new property of supersonic conical flows is realized in the presence of a branched shock system is determined. |
