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A Limiting Solution for Flow Past a Delta Wing in the Presence of Supercritical Flow Regions

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Abstract

The flow past a planar delta wing is studied for strong interaction between the boundary layer and the outer supersonic flow. An analytic investigation is carried out using the “Newtonian” passage to the limit in which the specific heat ratio tends to unity and the Mach and Reynolds numbers to infinity. Possible flow regimes are classified for various wing aspect ratios. For determining the supercritical-subcritical flow transition line an analytic expression, correct to the second approximation, is obtained for flow past a cold wing with a fairly large aspect ratio in which the transverse boundary-layer flows are insignificant.

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REFERENCES

  1. V.Ya. Neiland, “On the theory of interaction between a hypersonic flow and a boundary layer for two-and three-dimensional separation flows. Part 1. Three-dimensional flows,” Uch. Zap. TsAGI, 5, No. 2, 70 (1974).

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  2. G.N. Dudin and V.Ya. Neiland, “Supercritical regime of hypersonic flow past a delta wing,” Zh. Prikl. Mekh.Tekhn. Fiz., No. 3, 100 (1985).

    Google Scholar 

  3. G.N. Dudin, “On the existence of self-similar solutions in the supercritical region on the delta wing in a hypersonic flow,” Izv. Ross. Akad. Nauk, Mekh. Zhidk. Gaza, No. 2, 156 (1997).

    Google Scholar 

  4. W. Hayes and R. Probstein, Hypersonic Flow Theory, Academic Press, New York (1959).

    Google Scholar 

  5. G. G. Chernyi, Introduction to Hypersonic Flow, Academic Press, New York (1961).

    Google Scholar 

  6. V. I. Smirnov, A Course of Higher Mathematics. Vol. 2 [in Russian], Gostekhizdat, Moscow (1958).

    Google Scholar 

  7. V.Ya. Neiland and L.A. Sokolov, “Laminar boundary layer on a cone at an angle of incidence in a hypersonic flow,” Tr. TsAGI, No. 1812, 3 (1977).

    Google Scholar 

  8. V.A. Bashkin and G.N. Dudin, Three-Dimensional Hypersonic Viscous Gas Flows [in Russian], Nauka, Moscow (2000).

    Google Scholar 

  9. H. Schlichting, Boundary Layer Theory, McGraw-Hill, New York (1968).

    Google Scholar 

  10. G.N. Dudin, “Calculation of equations of a laminar boundary layer on the line of symmetry of a slender delta wing,” Tr. TsAGI, No. 2046, 58 (1980).

    Google Scholar 

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Authors
  1. G. N. Dudin
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  2. V. Ya. Neiland
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Dudin, G.N., Neiland, V.Y. A Limiting Solution for Flow Past a Delta Wing in the Presence of Supercritical Flow Regions. Fluid Dynamics 37, 939–950 (2002). https://doi.org/10.1023/A:1022308615249

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  • DOI: https://doi.org/10.1023/A:1022308615249

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