小型超音速実験機(ジェット実験機)第2次形状インテークの空力設計と単体空力特性取得風洞試験

• 資料種別: 規格・テクニカルリポート類
• タイトル: 小型超音速実験機(ジェット実験機)第2次形状インテークの空力設計と単体空力特性取得風洞試験
• 著者・編者: 村上, 哲; 渡辺, 安; 藤原, 仁志; Murakami, Akira; Watanabe, Yasushi; Fujiwara, Hitoshi
• 著者標目: 村上, 哲; 渡辺, 安; 藤原, 仁志; Murakami, Akira; Watanabe, Yasushi; Fujiwara, Hitoshi
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 2003-06
• 出版年（W3CDTF）: 2003-06
• 並列タイトル等: Aerodynamic design and wind tunnel tests of 2nd configuration air-intake for jet-powered supersonic experimental airplane
• タイトル（掲載誌）: 航空宇宙技術研究所資料
• 巻号年月日等（掲載誌）: 774
• 掲載巻: 774
• ISSN（掲載誌）: ISSN : 1347-460X
• 本文の言語コード: jpn
• 件名標目: 空力特性; 風洞試験; 超音速航空機; 超音速インテーク; 空力設計; CFD; マッハ数; aerodynamic characteristic; wind tunnel test; supersonic aircraft; supersonic air intake; aerodynamic design; Mach number
• 対象利用者: 一般
• 一般注記: The Jet-Powered Supersonic Experimental Airplane (NEXST-2) being developed by the National Aerospace Laboratory (NAL) will have a high-speed propulsion system with two-dimensional external compression air-intake with variable ramps. This report describes the aerodynamic design of the NEXST-2 second configuration air-intake (C313 air-intake) and its wind tunnel test results. The C313 air-intake was designed at a Mach number of 2.0, using both a 1D empirical estimation method and 3D CFD analysis. The main objective of the wind tunnel tests was to obtain the aerodynamic characteristics required to estimate the performance of the propulsion system, and develop the air-intake control system. The wind tunnel tests were performed in Mach numbers ranging from 0.6 to 2.1 at the 2 m x 2 m Transonic Wind Tunnel and 1 m x 1 m Supersonic Wind Tunnel at NAL. The wind tunnel model is a 19.2 percent scale isolated C313 air-intake model. The aerodynamic characteristics obtained in the wind tunnel tests are in reasonable agreement with those predicted by the CFD analysis used for the aerodynamic design, so aerodynamic performance such as pressure recovery and distortion at the engine face met the design target. At higher Mach numbers (Mo greater than 1.8) however, buzz initiated by Ferri-instability was observed at a relatively high mass flow ratio in subcritical conditions. Consequently the stable margin in subcritical operations was smaller at higher Mach numbers. The test results also indicated that the state of air-intake flow could be appropriately correlated with the pressure ratio in the bleed plenum chamber to the freestream total pressure, used for the air-intake control. Side-wash upstream of the air-intake did not affect the aerodynamic performance at side-wash angles of less than 4 degrees.; 資料番号: AA0047394000; レポート番号: NAL TM-774
• オンライン閲覧公開範囲: インターネット公開
• 掲載誌（NCID）: AN00314334; https://ci.nii.ac.jp/ncid/AN00314334
• 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: 航空宇宙技術研究所が開発を進めているジェットエンジンを搭載した小型超音速実験機(ジェット実験機)には、マッハ2までの飛行速度で作動する2次元外部圧縮型可変形状超音速インテークを搭載する予定としている。ジェット実験機の推進システム性能予測およびインテーク可変制御開発に必要なインテーク空力特性を取得する...