Tokugawa N, Kwak D, Yoshida K, Ueda Y (2008) Transition measurement of natural laminar flow wing on supersonic experimental airplane (NEXST-1). Thomas ASW (1985) Aircraft drag reduction technology-a summary. The International Air Transport Association (2021) Aviation & climate change fact sheet. The Intergovernmental Panel on Climate Change (2021) AR6 climate change 2021: the physical science basis. Takaki R, Yamamoto K, Yamane T, Enomoto S, Mukai J (2003) The development of the UPACS CFD environment, high performance computing. Ohnuki T, Hirako K, Sakata K (2006) National experimental supersonic transport project. Nomura T (2019) Aerodynamic design of a 120-seat class passenger aircraft at cruise. Nomura T (2013) Conceptual design of future passenger aircraft aimed at reducing fuel consumption. Matsushima K, Iwamiya T, Nakahashi K (2004) Wing design for supersonic transports using integral equation method. Lynde MN, Campbell RL, Rivers MB, Viken SA, Chan DT, Watkins AN, Goodliff SL (2019) Preliminary results from an experimental assessment of a natural laminar flow design method. Lehner S, Crossley W (2008) Combinatorial optimization to include greener technologies in a short-to-medium range commercial aircraft. In: Proceedings of greener aviation 2016, paper no.180 Kwak D, Nomura T, Tokugawa N, Kurita M, Murayama M (2016b) Introduction of research project for environmental conscious aircraft technology in JAXA. In: 2016 Asia-Pacific international symposium on aerospace technology Kwak D, Arizono H, Nomura T (2016a) Studies on the lift distribution and aspect ratio for the fuel consumption reduction on subsonic aircraft. Iyer V (1993) Three-dimensional boundary layer program (B元D) for swept subsonic or supersonic wings with application to laminar flow control. Ishikawa H, Ueda Y, Tokugawa N (2017) Natural laminar flow wing design for a low boom supersonic aircraft. J Jpn Soc Aero Space Sci 64:113–122 (in Japanese) Ishikawa H, Tokugawa N, Ueda Y, Ito K, Yoshida K (2016) Development of inverse design system for supersonic natural laminar flow wing on high reynolds number condition. Hirose N, Takanashi S, Kawai N (1985) Transonic airfoil design based on Navier–Stokes equation to attain arbitrarily specified pressure distribution-an iterative procedure. Hashimoto A, Murakami K, Aoyama T, Ishiko K, Hishida M, Sakashita M, Lahur P (2012) Toward the fastest unstructured CFD code ‘FaSTAR’. NASA TP-3260Ĭollier FS, Thomas R, Nickol CA, Lee C-M, Tong M (2010) Environmentally responsible aviation-real solutions for environmental challenges facing aviation. IFASD-2017-008Ĭampbell RL (1992) An approach to constrained aerodynamic design with application to airfoils. KeywordsĪrizono H, Kwak D-Y, Nomura T (2017) Aerodynamics and structural design studies for fuel consumption reduction on subsonic aircraft. The objective of the natural laminar flow wing design of the Japan Aerospace Exploration Agency has been achieved. This result shows that the natural laminar flow wing design technology of the Japan Aerospace Exploration Agency is effective for highly swept wings. In both cases, the laminar flow region was extended by more than 20% in the area. A natural laminar flow design was successfully achieved for not only the main wing but also the vertical tail plane. A natural laminar flow design was carried out more efficiently with the help of various innovations. An automatic inverse design system with inverse problem design tools and flow solvers outside of the system was developed. The natural laminar flow wing design was applied to highly swept wings, such as the main wing and the vertical tail plane of TRA2022, which is defined as a 120-pax technical reference aircraft in subsonic aircraft research of the Japan Aerospace Exploration Agency. Natural laminar flow design has been applied to the next generation of subsonic aircraft, which are expected entry into service in the 2020s, with the aim of reducing greenhouse gas emissions, which is one of the Sustainable Development Goals.
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