リフティングボディ型再突入機 遷音速、超音速及び極超音速風洞試験

• 資料種別: 規格・テクニカルリポート類
• タイトル: リフティングボディ型再突入機 遷音速、超音速及び極超音速風洞試験
• 著者・編者: 川戸, 博史; 渡辺, 重哉; 藤井, 謙司; Kawato, Hiroshi; Watanabe, Shigeya; Fujii, Kenji
• 著者標目: 川戸, 博史; 渡辺, 重哉; 藤井, 謙司; Kawato, Hiroshi; Watanabe, Shigeya; Fujii, Kenji
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 2003-08
• 出版年（W3CDTF）: 2003-08
• 並列タイトル等: Transonic, supersonic and hypersonic wind tunnel tests of a lifting-body type reentry vehicle
• タイトル（掲載誌）: 航空宇宙技術研究所報告
• 巻号年月日等（掲載誌）: 1468
• 掲載巻: 1468
• ISSN（掲載誌）: ISSN : 1347-4588
• 本文の言語コード: jpn
• 件名標目: 風洞試験; 亜音速流; 極超音速流; リフティングボディ型再突入機; 空力特性; 超音速流; 構造安定性; エレボン; ラダー; wind tunnel test; subsonic flow; hypersonic flow; lifting-body type reentry vehicle; aerodynamic characteristic; supersonic flow; structural stability; elevon; rudder
• 対象利用者: 一般
• 一般注記: A series of wind tunnel tests from subsonic to hypersonic speeds were conducted to investigate the aerodynamic characteristics of a lifting-body type configuration for reentry vehicles and to accumulate knowledge and experience for the design of such vehicles. The tests were conducted at the NAL 2 m x 2 m Transonic Wind Tunnel for Mach numbers from 0.5 to 1.4 and at the NAL 1 m x 1 m Supersonic Wind Tunnel for numbers 1.4 to 4.0. For hypersonic speed of about Mach 10, the test was conducted at the 1.27 m Hypersonic Wind Tunnel. Data were obtained for the baseline configuration and several derived configurations to ascertain the effect of configuration modifications. The effectiveness of control surfaces such as elevons and rudders was also investigated. The test data indicated fin-induced nonlinear characteristics for the baseline configuration at transonic speeds. Data also indicated that enlarging the leading edge sweepback angle of the outboard fins from 41 deg. to 60 deg. or upsweeping the upper aft surface of the fuselage 20 deg., like an upward deflection of a control surface, improves the nonlinear characteristics. For the hypersonic test, a pitch down trend at angles of attack from 15 deg. to 22 deg. was observed for all configurations (with a pitch up trend for other angles of attack). No significant effect was observed for upper surface modification at hypersonic speeds, however, enlarging the fin cant angle from 20 deg. to 45 deg., improved the directional stability.; 資料番号: AA0047388000; レポート番号: NAL TR-1468
• オンライン閲覧公開範囲: インターネット公開
• 掲載誌（NCID）: AN00311347; https://ci.nii.ac.jp/ncid/AN00311347
• 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: リフティングボディ型再突入機の空力特性を取得し、形状設計のためのデータや経験を蓄積するために、亜音速から極超音速の範囲で風洞試験を実施した。風試はM=0.5〜1.4についてはNAL 2m×2m遷音速風洞で実施し、M=1.4〜4.0についてはNAL 1m×1m超音速風洞で実施した。またM=10程度の極...