Aerodynamical designing of the second generation Supersonic Transport (SST-2)

• 資料種別: 規格・テクニカルリポート類
• タイトル: Aerodynamical designing of the second generation Supersonic Transport (SST-2)
• 著者・編者: Vasiliev, L. E.
• 著者標目: Vasiliev, L. E.
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 2000-12
• 出版年（W3CDTF）: 2000-12
• 並列タイトル等: 第2世代超音速輸送機(SST-2)の空力設計
• タイトル（掲載誌）: 航空宇宙技術研究所特別資料
• 巻号年月日等（掲載誌）: 49T
• 掲載巻: 49T
• 掲載ページ: 21-42
• ISSN（掲載誌）: ISSN : 0289-260X
• 本文の言語コード: eng
• 件名標目: SST; 超音速輸送機; 空力設計; 2領域機; ストレーキ; CPW; 複合平面型翼; ソニックブーム; supersonic transport; aerodynamical design; two regime plane; complex planform wing; strake; sonic boom
• 対象利用者: 一般
• 一般注記: 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; The second generation of Supersonic Transport (SST-2) is required to have higher effectiveness than that of SST-1. The SST-2 should be the two-regime plane that has the equal range of flight at subsonic and supersonic cruise M numbers. Further the noise should be reduced at the take-off and landing. The investigation by TsAGI (The Central Aerodynamics Institutes) showed that these contradictory requirements might be satisfied with the CPW (Complex Planform Wings) concept in design. The CPW is consisted of a base wing with moderate aspect ratio and an additional wing (strake) with considerably small aspect ratio. A lifting surface with a given arrangement of the aerodynamic centers can be realized by appropriate choice of geometrical parameters. The SST-2 must be designed to be capable of transporting the passengers of 300 to 350 and have the range of 9,200 km. In order to satisfy these specifications, the aerodynamic designs should be optimized to increase the lift to drag ratio in the whole flight regime. The computational results based on linear theory methods showed that the gain in lift to drag ratios increased with the sweptback angle of strake and reached at a maximum value. It was shown that SST-2 designed as two-regime plane had the same values of range parameter at both subsonic and supersonic regions, which means the same fuel consumption at the both regimes. Further the take-off characteristics and wing devices, and sonic boom levels are described. Finally the main data of the baseline of Russian SST-2 are shown.; 資料番号: AA0028638003; レポート番号: NAL SP-49T
• オンライン閲覧公開範囲: インターネット公開
• 掲載誌（NCID）: AN10097345; https://ci.nii.ac.jp/ncid/AN10097345
• 連携機関・データベース: 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• 提供元機関・データベース: 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ

• 要約等: 第2世代の超音速輸送機(SST-2)にはSST-1より高い効率性が要求されている。SST-2は亜音速および超音速巡航マッハ数で等しい航続距離を持つ2領域機である。また、離着陸時の騒音を低減しなければならない。TsAGI(中央流体力学研究所)の研究は、これらの矛盾する要求を、設計におけるCPW(複合平...