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Cambered wing of small aspect ratio near a boundary surface

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Abstract

Flow of an inviscid fluid past a thin longitudinally cambered wing of small aspect ratio near a solid or free (case of a hydrofoil) surface is investigated. The possibility of using a cylindrical twist (camber) of the wing to provide the necessary longitudinal trim and to reduce drag at a given lift is analyzed. The investigation is conducted by slender-body theory methods.

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Literature cited

  1. J. Nielsen, Missle Aerodynamics, McGraw-Hill (1960).

  2. E. V. Bulygina, “Self-balancing of supersonic wings with variable sweepback at the leading edge,” Izv. Vuzov, Aviats. Tekh., No. 4 (1960).

  3. N. P. Korobeinikov, “Calculation of the aerodynamic characteristics of thin curved bodies and cambered wings,” Izv. Vuzov, Aviats. Tekh., No. 3 (1961).

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Authors and Affiliations

  1. Khar'kov

    V. I. Kholyavko

Authors
  1. V. I. Kholyavko
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 49–55, November–December, 1971.

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Kholyavko, V.I. Cambered wing of small aspect ratio near a boundary surface. Fluid Dyn 6, 951–957 (1971). https://doi.org/10.1007/BF01019800

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  • DOI: https://doi.org/10.1007/BF01019800

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