Numerical Calculation of Scramjet Inlet Flow

• 資料種別: 規格・テクニカルリポート類
• タイトル: Numerical Calculation of Scramjet Inlet Flow
• 著者・編者: 石黒, 登美子; 小川, 哲; 和田, 安弘; ISHIGURO, Tomiko; OGAWA, Satoru; WADA, Yasuhiro
• 著者標目: 石黒, 登美子; 小川, 哲; 和田, 安弘; ISHIGURO, Tomiko; OGAWA, Satoru; WADA, Yasuhiro
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 1992-07
• 出版年（W3CDTF）: 1992-07
• タイトル（掲載誌）: Technical Report of National Aerospace Laboratory TR-1174T
• 巻号年月日等（掲載誌）: 1174T
• 掲載巻: 1174T
• 掲載ページ: 29-
• ISSN（掲載誌）: ISSN : 0389-4010
• 本文の言語コード: eng
• 件名標目: hypersonic flow; supersonic flow; scramjet inlet
• 対象利用者: 一般
• 一般注記: A numerical procedure to analyze flowfields through and around the Langley-type scramjet engine inlet is proposed. To accurately treat boundary conditions(walls, edge, etc.), all boundaries are mapped onto certain parts of the faces of three rectangular parallelepipeds. A computational space is made by connecting them. The three-dimensional full Navier-Stokes equations which include the Baldwin-Lomax algebraic turbulent model are solved by applying the TVD scheme to the uniform mesh points of the space. To exhibit capability of the numerical procedure, parametric studies on flow simulations were carried out by fixing freestream Reynolds number Re=ρ∞c∞L/μ∞=5.3×10(exp 5) under various trios of a freestream Mach number M∞, a sweep angle of leading edge of side plate β, and an entrance/throat contaction ratio R(M∞=2～10,β=0deg～60deg ,R=3～10). The influence of the parameters on inlet performances(a mass capture ratio, a total pressure recovery ratio, and possibility of starting) is discussed. The results are in good agreements with the experiments under M∞=4 in starting cases, where iterated reflective oblique shock waves made by wedges of side panels decelerate and compress air. Unstarting phenomenon was analyzed in cases either of low M∞ or high R. To addition, an unstarting flowfield was obtained in the computation of incoming flow condition with a thick boundary layer attached to the upper wall or with a small freestream Reynolds number. If the unstarting was caused by viscosity, a large subsonic recirculation region grows just under the upper wall in upstream region of the throat. A separation shock wave which emanates from the upstream end of region prevents the formation of a interative weak shock wave system.; 資料番号: NALTR1174000; レポート番号: NAL TR-1174T
• オンライン閲覧公開範囲: インターネット公開
• 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: ラングレー型スクラムジェットエンジン空気取入口の流れ場を解析するための計算手法を提示する。壁や縁のような境界条件を正確に取り扱うために,総ての境界は三つの直方体の表面に写像し,計算空間はそれらを結びつけることによって作る。Baldwin-Lomax代数渦粘性モデルを含ませた完全Navier-Stok...