The development of a new viscous shock-layer code for computing hypersonic flows around blunted body and its applications

• 資料種別: 規格・テクニカルリポート類
• タイトル: The development of a new viscous shock-layer code for computing hypersonic flows around blunted body and its applications
• 著者・編者: 口石, 茂; Kuchiishi, Shigeru
• 著者標目: 口石, 茂; Kuchiishi, Shigeru
• 出版事項: 宇宙航空研究開発機構
• 出版年月日等: 2005-10-03
• 出版年（W3CDTF）: 2005-10-03
• 並列タイトル等: 鈍頭物体周り極超音速流計算用新規粘性衝撃層コードの開発およびその応用
• タイトル（掲載誌）: 宇宙航空研究開発機構研究開発報告
• 巻号年月日等（掲載誌）: JAXA-RR-05-001E
• 掲載巻: JAXA-RR-05-001E
• ISSN（掲載誌）: ISSN : 1349-1113
• 本文の言語コード: eng
• 件名標目: 極超音速流; 粘性衝撃層解析; 淀み流線; 衝撃層; 熱力学的性質; 鈍頭物体; 化学反応モデル; ベンチマーク試験; 数値解析; ナビエ-ストークス方程式; 計算機プログラミング; hypersonic flow; viscous shock layer analysis; stagnation streamline; shock layer; thermodynamic property; blunted body; chemical reaction model; benchmark test; numerical analysis; Navier-Stokes equation; computer programming
• 対象利用者: 一般
• 一般注記: A numerical code has been developed to solve the Viscous Shock-Layer (VSL) equations for chemically reacting hypersonic flows around a blunted body. The code basically follows the original solution procedure found in other VSL codes, but some specific treatments have been considered and implemented to enhance the accuracy and robustness. In the present article, the governing equations and physical models employed are firstly presented and then the method of solution is described in detail. By using the present code, it has become possible to solve chemically nonequilibrium flows around a hemisphere typically within 1 minute using a conventional personal computer. The accuracy of the code is validated by comparing with the computational results of other VSL/Navier-Stokes codes and available experimental data. It is shown that the difference between Navier-Stokes results in the stagnation heat flux for perfect gas flow is around 1 percent at most for a Reynolds number range from 10(exp 3) to 10(exp 5). Further, an approach to solving stagnation streamline profiles both quickly and accurately under the framework of the present VSL algorithm is proposed and its accuracy and availability are examined. Also proposed is an algorithm which computes the free stream properties of ground-based high enthalpy test facilities from the measured stagnation point heat flux and Pitot pressure as an inverse problem of the VSL analysis. The stagnation point analysis method developed is implemented in this algorithm and the accuracy and reliability of this approach are examined.; 資料番号: AA0049037000; レポート番号: JAXA-RR-05-001E
• オンライン閲覧公開範囲: インターネット公開
• 掲載誌（NCID）: AA1192675X; https://ci.nii.ac.jp/ncid/AA1192675X
• 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: 鈍頭物体周り極超音速化学反応流に関する粘性衝撃層(VSL)方程式の数値解析コードが開発された。本コードは基本的に過去に提案されたVSL解法に従っているが、精度および安定性向上の目的でいくつかの改良が試みられている。本論文では、基礎方程式および物理モデルについてまず記述され、次に解法の詳細が述べられる...