Abstract
Options for constructing a grid with an edge selection and setting the conditions for the conicity of the flow relative to the edge are offered to simulate the flow around conical bodies with a sharp supersonic edge. Methods for constructing a grid near a star-shaped body, a flat and V- or Λ-shaped wing, near a wing with a central body, and a V-shaped wing with a leading edge of negative sweep have been implemented. The boundary condition for the flow conicity relative to the edge is sufficient for constructing a solution. Calculations of the flow around several variants of geometries of bodies of various types with a fixed midsection area and wing span are carried out, their aerodynamic characteristics are compared.
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Acknowledgements
The calculations were carried out on the MVS-100K supercomputer of the Interdepartmental Supercomputer Center of the Russian Academy of Sciences.
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Maksimov, F.A. (2022). Simulation of Flows Near Wings with Supersonic Edges. In: Favorskaya, M.N., Nikitin, I.S., Severina, N.S. (eds) Advances in Theory and Practice of Computational Mechanics. Smart Innovation, Systems and Technologies, vol 274. Springer, Singapore. https://doi.org/10.1007/978-981-16-8926-0_7
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DOI: https://doi.org/10.1007/978-981-16-8926-0_7
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