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Simulation of leading-edge vortex flows

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Abstract

An implicit upwind-relaxation finite-difference algorithm solving the incompressible Navier-Stokes equations is employed to simulate low-speed, three-dimensional, laminar, leadingedge vortex flows over three round-edged low-aspect-ratio wings. The effects of grid density, angle of attack, Reynolds number, and wing planform on the flowfield structures and integral values are studied. Computed results are presented and compared with experimental data.

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Authors and Affiliations

  1. Vigyan Inc, 23666, Hampton, VA, U.S.A.

    C.-H. Hsu

  2. Theoretical Flow Physics Branch, NASA Langley Research Center, 23665, Hampton, VA, U.S.A.

    C. H. Liu

Authors
  1. C.-H. Hsu
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  2. C. H. Liu
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Additional information

Communicated by M.Y. Hussaini

The work of the first author was supported by the NASA Langley Research Center under Contract NAS1-18585.

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Hsu, CH., Liu, C.H. Simulation of leading-edge vortex flows. Theoret. Comput. Fluid Dynamics 1, 379–390 (1990). https://doi.org/10.1007/BF00271797

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  • DOI: https://doi.org/10.1007/BF00271797

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