ИСТИНА

The results of numerical and experimental studies of an asymmetric flow about the diamond-shaped wings at regimes with attached shock waves or centered rarefaction waves at the leading edges at Mach numbers M=3-10 are presented. The computational codes of the second-order approximation on special grids have been developed within the ideal gas model. These codes have allowed to obtain the original data on the asymmetric flow about the diamond-shaped wings. A wide range of flow schemes in the shock layer, depending on the Mach number, angles of attack and slip, due to the presence of the salient point of the wing transverse contour, has been found, in particular, the windward console separation and a vortex presence in the flow regimes with sideslip and subsonic (transverse) flow in the vicinity of the central wing chord, the existence of trans- and supersonic flow along the vortex perimeter and in the return flow near the leeward console wall with the formation of shock waves with increasing slip angle. For one of the flow schemes sequences, which happens at moderate Mach numbers of undisturbed flow with increasing slip angle, the convergence of the current spreading point, closing the vortex, and the of the current lines node on the leeward console surface is characteristic. Within the conditions in the vicinity of the salient point, allowing the existence of a centered rarefaction wave, the vortex moves downstream along the wing surface, and a shock wave is formed in front of it. After the "merging" of the spreading point and the current lines node on the leeward console remain only the draining point, to which lead the current lines, extending from the wing front edge, and the vortex Ferry feature above it. At hypersonic Mach numbers and high angles of slip, only the of the current lines node is realized on the leeward console surface. The existence of flow schemes with a vortex formation on the wing leeward console in the central chord vicinity has been confirmed in experiments at the number M=3, using various methods, in particular, a special shadowgraph method for conical flows visualization. The numerical studies results of the ability to control the flow structure about a diamondshaped wing with sideslip. A half-angle of a circular cone, inscribed in the inner dihedral angle between the flat wing consoles, is used as a control parameter to eliminate the of its surface fracture at the central chord. It has been shown that in the flow with sideslip this method of control is effective for eliminating the vortex structures on the leeward wing console, that in the conical flow generate the critical lines on a surface with intense flow spreading. In the neighborhood of these lines high heat flows can be realized in the real flow. The classification of vortex structures in the shock layer in the presence of rounding in the neighborhood of the wing symmetry plane has been made. The research has been conducted with partial financial support of RFBR (project 18-01-00182).