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Separated flow over a strongly cambered conical wing at small angles of attack

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Abstract

The interference of supersonic flows on the concave surface of conical wings was experimentally investigated in [1] for various values of the camber and angles of attack. In order to establish the detailed structure of the interference flow the laminar flow past a wing model in the form of half the surface of a circular cone with vertex angle 2θk = 34° was numerically modeled within the framework of the quasiconical approximation for the three-dimensional Navier-Stokes equations [2]. Under this assumption, confirmed by analysis of the experimental data [1], it was found that the displacement of the external inviscid flow as a result of intense flow separation beyond the leading edges leads to flow patterns similar to those realized on V wing's with a break in the transverse contour [3]. At nonzero angles of attack weak secondary separation was detected beneath the flattened regions of primary separation located in the shaded parts of the concave surface.

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Literature cited

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Authors and Affiliations

  1. Dnepropetrovsk

    V. L. Borshch & V. V. Kravets

Authors
  1. V. L. Borshch
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  2. V. V. Kravets
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 130–136, July–August, 1989.

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Borshch, V.L., Kravets, V.V. Separated flow over a strongly cambered conical wing at small angles of attack. Fluid Dyn 24, 599–604 (1989). https://doi.org/10.1007/BF01052424

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  • DOI: https://doi.org/10.1007/BF01052424

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