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Volume 41 Issue 9
Sep.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(9): 1608-1614.
GAN Wenbiao, ZHOU Zhou, XU Xiaopinget al. Aerodynamic design of high-aspect-ratio flying wing based on criteria[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1608-1614. doi: 10.13700/j.bh.1001-5965.2014.0672(in Chinese)
Citation: GAN Wenbiao, ZHOU Zhou, XU Xiaopinget al. Aerodynamic design of high-aspect-ratio flying wing based on criteria[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1608-1614. doi: 10.13700/j.bh.1001-5965.2014.0672(in Chinese)
shu

Aerodynamic design of high-aspect-ratio flying wing based on criteria

doi: 10.13700/j.bh.1001-5965.2014.0672
  • 1.

    Research Institute of Unmanned Aerial Vehicle, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. College of Aeronautic, Northwestern Polytechnical University, Xi'an 710072, China

  • Received Date: 30 Oct 2014
  • Publish Date: 20 Sep 2015
    Abstract
  • To improve aerodynamic performance of flying wing from design reality, aerodynamic design and analysis of high-aspect-ratio flying wing unmanned aerial vehicle (UAV) were conducted. In design and analysis process, according to features of flying wing, aerodynamic design criteria have been proposed. Based on design criteria, a design optimization framework, using updated design strategies, was built which combined variable fidelity numerical simulation and surrogated model optimization method. Flying wing UAV was carried out with parametric expression, automatic mesh generation of transfinite interpolation (TFI), and multi-round optimization. And then recommended configuration was obtained and validated for detailed aerodynamic performance by γ-Reθt transition model method. The results show that design configuration of flying wing UAV agrees well with design criteria, cruise lift-to-drag ratio of UAV increases 14% compared to the original configuration, γ-Reθt transition model method can analyze the detailed aerodynamic characteristics of high-aspect-ratio flying wing UAV.

     

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