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Combined influence of the mach and Reynolds numbers on transition in the boundary layer

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Literature cited

  1. Modern Problems of Gasdynamics [Russian translation], Mir, Moscow (1971).

  2. S. R. Pate and C. J. Schueler, “Radiated aerodynamic noise effects on boundary-layer transition in supersonic and hypersonic wind tunnels,” AIAA J.,7, No. 9 (1969).

  3. J. L. Potter and J. D. Whitfield, “Effect of slight nose bluntness and roughness on boundary-layer transition in supersonic flows,” J. Fluid Mech.,12 (1962).

  4. R. Michel and V. Schmitt, Resultats sur la region de transition de la couche limite hypersonique,” L'Aeronautique et l'Astronautique, No. 19 (1970).

  5. H. H. Heller, “Acoustic technique for detection of flow transition on hypersonic reentry vehicles,” AIAA J.,7, No. 12 (1969).

  6. J. L. Potter, “Observations on the influence of ambient pressure on boundary-layer transition,” AIAA J.,6, No. 10 (1968).

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  8. G. G. Mateer and H. K. Larson, “Unusual boundary-layer transition results on cones in hypersonic flow,” AIAA J.,7, No. 4 (1969).

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Authors and Affiliations

  1. Novosibirsk

    V. G. Pridanov, A. M. Kharitonov & V. V. Chernykh

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  1. V. G. Pridanov
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  2. A. M. Kharitonov
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  3. V. V. Chernykh
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 160–164, January–February, 1974.

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Pridanov, V.G., Kharitonov, A.M. & Chernykh, V.V. Combined influence of the mach and Reynolds numbers on transition in the boundary layer. Fluid Dyn 9, 126–129 (1974). https://doi.org/10.1007/BF01016321

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  • DOI: https://doi.org/10.1007/BF01016321

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