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Flow in the hypersonic boundary layer on a finite triangular wing in the presence of an angle of attack

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Literature cited

  1. A. H. Whitehead, Jr., J. N. Hefner, and D. M. Rao, “Lee-surface vortex effects over configurations in hypersonic flow,” AIAA Paper No. 72-77 (1972).

  2. D. M. Rao and A. H. Whitehead, Jr., “Lee-side vortices on delta wings at hypersonic speeds,” AIAA J.,10, No. 11 (1972).

  3. E. J. Cross, Jr., and W. L. Hankey, “Investigation of leeward side of a delta wing at hypersonic speeds,” AIAA Paper No. 68-675 (1968).

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  6. V. Ya. Neiland, “On the theory of hypersonic flow interaction with the boundary layer for two- and three-dimensional separation flows. Pt. 2, Two-dimensional flows and a delta wing,” Uch. Zap. TsAGI,5, No. 3 (1974).

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

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  1. Moscow

    G. N. Dudin

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  1. G. N. Dudin
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Translated from Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, No, 3, pp. 108–113, May–June, 1983.

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Dudin, G.N. Flow in the hypersonic boundary layer on a finite triangular wing in the presence of an angle of attack. J Appl Mech Tech Phys 24, 383–388 (1983). https://doi.org/10.1007/BF00909759

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  • DOI: https://doi.org/10.1007/BF00909759

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