title: On mathematical modeling of a hypersonic flow past a thin wing with variable shape
metadata.name: dc.contributor.author
metadata.value: Bogatko, Vsevolod I.
metadata.lang: -
metadata.name: dc.contributor.author
metadata.value: Potekhina, Elena A.
metadata.lang: -
metadata.name: dc.date.accessioned
metadata.value: 2022-02-16T19:31:31Z
metadata.lang: -
metadata.name: dc.date.available
metadata.value: 2022-02-16T19:31:31Z
metadata.lang: -
metadata.name: dc.date.issued
metadata.value: 2021-12
metadata.lang: -
metadata.name: dc.identifier.citation
metadata.value: Bogatko V. I., Potekhina E.A. On mathematical modeling of a hypersonic flow past a thin wing with variable shape. Vestnik of Saint Petersburg University. Mathematics. Mechanics. Astronomy, 2021, vol. 8 (66), issue 4, pp. 639–645.
metadata.lang: en_GB
metadata.name: dc.identifier.other
metadata.value: https://doi.org/10.21638/spbu01.2021.409
metadata.lang: -
metadata.name: dc.identifier.uri
metadata.value: http://hdl.handle.net/11701/35111
metadata.lang: -
metadata.name: dc.description.abstract
metadata.value: The present work is devoted to a further study of the spatial flowing of a thin wing of
  variable shape by a hypersonic flow of non-viscous gas. The head shock wave is considered
  to be attached to the leading edge of the wing. The use of the thin shock layer method for
  solving the system of gas dynamics equations makes it possible to build a mathematical
  model of the flow in question. It should also be noted that the analysis of boundary conditions
  makes it possible to determine the structure of the expansion of the quantities sought
  in a series and to construct approximate analytical solutions. In this case, in determining
  the first approximation corrections, two equations are integrated independently of the other
  equations. The application of the Euler—Ampere transform allows to construct a solution
  depending on two arbitrary functions and an unknown of the shock front. To determine
  these functions, previously it was obtained an integro-differential system of equations. This
  paper proposes one of the variants of the semi-inverse method for constructing the solution
  of this system, in which the form of one of arbitrary function is given. This approach
  allows you to additionally set the equation for the leading edge of the wing, and in the
  case when the head wave is attached along the entire leading edge and the inclination of
  the wing surface on it. The variant of the semi-inverse method presented in the work for
  the non-stationary spatial problem of the flow has made it possible to obtain a particular
  solution, which is a model for various flow regimes around the wing. Formulas are obtained
  to determine: the shape of the front of the shock wave, the shape of the surface of the
  streamlined body, the distance between the shock wave and the surface of the body, and
  the flow parameters on the wing surface.
metadata.lang: en_GB
metadata.name: dc.language.iso
metadata.value: ru
metadata.lang: en_GB
metadata.name: dc.publisher
metadata.value: St Petersburg State University
metadata.lang: en_GB
metadata.name: dc.relation.ispartofseries
metadata.value: Vestnik of St Petersburg University. Mathematics. Mechanics. Astronomy;Volume 8 (66); Issue 4
metadata.lang: -
metadata.name: dc.subject
metadata.value: mathematical modeling
metadata.lang: en_GB
metadata.name: dc.subject
metadata.value: hypersonic flowing of bodies
metadata.lang: en_GB
metadata.name: dc.subject
metadata.value: unsteady flows
metadata.lang: en_GB
metadata.name: dc.subject
metadata.value: partial differential equations
metadata.lang: en_GB
metadata.name: dc.subject
metadata.value: small parameter
metadata.lang: en_GB
metadata.name: dc.title
metadata.value: On mathematical modeling of a hypersonic flow past a thin wing with variable shape
metadata.lang: en_GB
metadata.name: dc.type
metadata.value: Article
metadata.lang: en_GB
resources.filename: 639-645.pdf
resources.url: https://dspace.spbu.ru/bitstream/11701/35111/1/639-645.pdf
resources.format: Adobe PDF
resources.size: 267,42 kB