The article is devoted to modeling the flow around a system of controlled wings (profiles) in an ideal incompressible fluid. The relevance of the studyis due to the need to develop a computational technology for determining in real time the scalar and vector characteristics of the controlled motion of a system of wings distributed in space, which form an oscillatory engine. The modes of motion of the wing system go beyond the limits of linear theory.A mathematical model of the circulating separation flow around the moving wings, which together with the vortex wake form the moving boundariesof the flow region, is presented. The computational technology is based on the application of the discrete singularity method. A model of unsteadyseparatedflow around a system of M thin profiles with a rounded leading edge is proposed, which takes into account the unsteady flow regime around the wing system. The numerical-analytical model for calculating the pressure field in the variable connectivity region has been improved, which allows determining both the instantaneous distributed aerohydrodynamic characteristics on each wing and the averaged integral AGDH of the wing system as a whole. A mathematical model for controlling the wing motion has been proposed, which significantly improves the energy efficiency and thrust characteristics of the oscillatory engine. In the system computational experiment, quantitative and qualitative regularities of the formation and evolution of the wake behind the system with controlled wing motion have been revealed, and the conditions for the emergence of coherent vortex structures have been determined. A comparison of the results of the computational experiment with the results of full-scale modeling has been presented.
Vasin et al. (Mon,) studied this question.