@techreport{oai:jaxa.repo.nii.ac.jp:00041428,
 author = {松島, 紀佐 and 岩宮, 敏幸 and Zhang, Wanqiu and Matsushima, Kisa and Iwamiya, Toshiyuki and Zhang, Wanqiu},
 month = {Dec},
 note = {航空宇宙技術研究所 17-19 Jan. 2000 東京 日本, National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan, NALの最初のSSTモデルに用いる翼の空力形状が、超音速逆設計法を用いて設計された。この手法は翼・胴体形状を取り扱い、各スパン位置での翼断面幾何形状を提供する。設計目標は、マッハ2の速度でのNLF(自然層流)翼の実現である。逆設計手法の最初の系を、いくつかの設計制約を満足するように修正しなければならい。この方法により、従来の設計法で設計したものよりずっと望ましい特性を持つように翼断面形状を設計した。NLF翼を実現する空力学については、修正した方法は良く機能する。設計翼の圧力分布は、目標圧力と良く一致した。制約については、その多くが修正した設計法を用いることで満たすことができる。しかし、厚さ制約制御の過程で困難さを見出した。圧力制約に対処する将来計画を論じた。, Aerodynamic shape of a wing for NAL (National Aerospace Laboratory)'s first SST model has been designed by a supersonic inverse design method. This method handles wing-fuselage configurations and provides wing section's geometry at every span for Navier-Stokes flowfields. The design target is an NLF (Natural Laminar Flow) wing at the speed of M(sub infinity) = 2.0. The original system of the inverse design method has to be modified so that several design constraints can be satisfied. By means of the method, a wing section shape has been designed to have much more desirable characteristics than that by the traditional design method. In terms of aerodynamics to realize an NLF wing, the modified method works very well. The pressure distribution of the designed wing shows good agreement with the target pressure. In terms of constraints, most of them can be satisfied in the modified design method; however, difficulty has been found during the process for thickness constraint control. The prospective strategy to cope with the thickness constraint is discussed., 資料番号: AA0028638012, レポート番号: NAL SP-49T},
 title = {Inverse wing design for the scaled supersonic experimental airplane with ensuring design constraints},
 year = {2000}
}