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Transonic Design of SST

To Employ Japanese SST as a Candidate for Near Sonic Transport
  • Kisa Matsushima
  • Wataru Yamazaki
  • Kazuhiro Nakahashi
Part of the Fluid Mechanics and its Applications book series (FMIA, volume 73)

Abstract

Aerodynamic analysis and optimization for an airplane cruising at near-sonic regime are discussed based on CFD simulations. Japanese experimental supersonic airplane, called NEXST-1, was employed as the baseline model. Aerodynamic characteristics obtained by the flow simulation indicated that the model was promising as a candidate for the sonic plane. The drag reduction design by optimizing wing warp was performed on the plane. The optimization process suggested the mechanism of design to reduce drag force. Key words: Near Sonic Transport, CFD, Aerodynamic Wing Design, Japanese SST

Keywords

Shock Wave Mach Number Drag Reduction Aerodynamic Performance Aerodynamic Design 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer Science+Business Media Dordrecht 2003

Authors and Affiliations

  • Kisa Matsushima
    • 1
  • Wataru Yamazaki
    • 1
  • Kazuhiro Nakahashi
    • 1
  1. 1.Dept. Aeronautics and Space EngineeringTohoku University Aza-aobaSendai, MiyagiJapan

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