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A visualization study of the near-wall behaviors of an oblique plate at different angles of attack

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Abstract

A combined method of oil flow visualization and smoke visualization with a laser sheet was conducted on an oblique plate with 64° sweep under different angles of attack. The oil flow visualization results reveal the characteristics of the flow pattern on the upper surface of the oblique plate, including the formation of separation, reattachment lines and the variation of these lines when the angle of attack changes. The smoke visualization results show the vortex structure above the oblique plate so as to demonstrate and interpret the flow pattern captured in the oil flow visualization.

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References

  • Hirschberg MJ, Hart DM, Beutner TJ (2007) A summary of a half-century of oblique wing research. In: Proceedings of the 45th AIAA aerospace sciences meeting and exhibit, AIAA-2007-150

  • Holdaway GH, Hatfield EW (1958) Transonic investigation of yawed wings of aspect ratio 3 and 6 with a Sear-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.2. NASA (NACA) TECHNICAL REPORTS, Do ID.19930090023

  • Jones RT (1972) Reduction of wave drag by antisymmetric arrangement of wings and bodies. AIAA J 10:171–176

    Article  Google Scholar 

  • Jones RT, Nisbet JW (1974) Transonic transport wings—oblique or swept? Astronaut Aeronaut J 12:40–47

    Google Scholar 

  • Kroo I, Wintzer M, Sturdza P (2006) Conceptual design of conventional and oblique wing configuration for small supersonic aircraft. In: Proceedings of the 44th AIAA aerospace science meeting and exhibit, 9−12 Jan, Reno, Nevada

  • Mehta U (1986) The computation of flow past an oblique wing using the thin-layer Navier–Stokes equations. NASA Technical Memorandum 88317

  • Sim AG, Curry RE (1984) Flight-determined aerodynamic derivatives of the AD-1 oblique-wing research airplane. NASA Technical Paper 2222

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Acknowledgments

This work was supported by the National Natural Science Foundation of China (NSFC No. 90816026).

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Authors and Affiliations

  1. Department of Modern Mechanics, University of Science and Technology of China, Hefei, 230027, People’s Republic of China

    Yun Liu, Wen Chao Yang & Ji Ming Yang

Authors
  1. Yun Liu
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  2. Wen Chao Yang
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  3. Ji Ming Yang
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Correspondence to Ji Ming Yang.

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Liu, Y., Yang, W.C. & Yang, J.M. A visualization study of the near-wall behaviors of an oblique plate at different angles of attack. J Vis 14, 141–148 (2011). https://doi.org/10.1007/s12650-011-0086-x

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  • DOI: https://doi.org/10.1007/s12650-011-0086-x

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