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Volume 40 Issue 4
Apr.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(4): 551-557.
Hu Shuyao, Jiang Chongwen, Gao Zhenxun, et al. Oblique flying wing supersonic airliner aerodynamic configuration parameters selection method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 551-557. doi: 10.13700/j.bh.1001-5965.2013.0291(in Chinese)
Citation: Hu Shuyao, Jiang Chongwen, Gao Zhenxun, et al. Oblique flying wing supersonic airliner aerodynamic configuration parameters selection method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 551-557. doi: 10.13700/j.bh.1001-5965.2013.0291(in Chinese)
shu

Oblique flying wing supersonic airliner aerodynamic configuration parameters selection method

doi: 10.13700/j.bh.1001-5965.2013.0291

  • National Laboratory for Computational Fluid Dynamics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 24 May 2013
  • Publish Date: 20 Apr 2014
    Abstract
  • The method is capable of providing the basic geometry of the flying wing simply by given certain bulk parameters, such as the passenger number, range, cruise velocity and height. Discussions were paid to the selection of the appropriate symmetry plane chord, the constraint of the wing span caused by the aspect ratio and take-off wing loading, the range identification of the aspect ratio and take-off wing loading, as well as the dimension derivations of the fuel tank and passenger cabin. In order to demonstrate the correlation between configuration parameters and design demands, several designed points were calculated using the present method under the conditions of 250-550 passengers and 6 500-10 000 km flight range, with lift-to-drag ratio of 11-12. The results yield that there exists a take-off weight threshold of the designed wing. When the take-off weight is less than the threshold value, minimum aspect ratio defines the wing area; whereas the take-off weight is larger than the value, maximum wing loading determines the wing area. Improvements on the cruise lift-to-drag ratio would lessen the wing area which can be decided by the maximum wing loading.

     

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