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
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© 2003 Springer Science+Business Media Dordrecht
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Matsushima, K., Yamazaki, W., Nakahashi, K. (2003). Transonic Design of SST. In: Sobieczky, H. (eds) IUTAM Symposium Transsonicum IV. Fluid Mechanics and its Applications, vol 73. Springer, Dordrecht. https://doi.org/10.1007/978-94-010-0017-8_48
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DOI: https://doi.org/10.1007/978-94-010-0017-8_48
Publisher Name: Springer, Dordrecht
Print ISBN: 978-94-010-3998-7
Online ISBN: 978-94-010-0017-8
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