後退円柱上の境界層に対するNavier-Stokesシミュレーションと線形安定解析

• Material Type: 規格・テクニカルリポート類
• Title: 後退円柱上の境界層に対するNavier-Stokesシミュレーションと線形安定解析
• Author/Editor: 野村, 聡幸; Nomura, Toshiyuki
• Author Heading: 野村, 聡幸; Nomura, Toshiyuki
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1997-02
• Publication Date (W3CDTF): 1997-02
• Alternative Title: Navier-Stokes simulation and linear stability analysis for a boundary layer on the swept cylinder
• Periodical title: 航空宇宙技術研究所報告
• No. or year of volume/issue: 1321
• Volume: 1321
• Pages: 1-14
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Subject Heading: 層流乱流遷移; 線形安定解析; ナビエ・ストークスコード; ナビエ・ストークス方程式; 付着線境界層; 無限後退円柱; シミュレータコード; 層流境界層制御; 高速民間輸送機; 抗力低減; 空間増幅率; 計算格子; 時間進行法; 速度プロファイル; 温度プロファイル; laminar turbulent transition; linear stability analysis; Navier Stokes code; Navier Stokes equation; attachment line boundary layer; infinite swept cylinder; simulator code; laminar flow boundary layer control; high speed civil transport; drag reduction; spatial growth rate; computational grid; time marching method; velocity profile; temperature profile
• Target Audience: 一般
• Note (General): Techniques to delay laminar-turbulent transition on the wing, called laminar-flow control, are important for drag reduction of high-speed civil transports cruising at supersonic speeds. The onset of transition is numerically predicted by computation of a boundary-layer flow, linear stability analysis for the flow, and integration of the spatial growth rates obtained by the analysis. Boundary-layer flows used to predict the transition have been generally computed with boundary-layer codes. In this paper, a Navier-Stokes code is constructed for the computation. The supersonic flow around an infinite swept cylinder is computed with three types of grids, which have different resolutions. The accuracy of the Navier-Stokes code is tested by comparing velocity, and temperature profiles in the boundary layer obtained with these three grids. Furthermore, linear stability analysis for the attachment-line boundary layer is performed. The unstable ranges obtained by the analysis agree well with the results of Malik (1988), which confirm the accuracy of the present Navier-Stokes code.; 資料番号: AA0001142000; レポート番号: NAL TR-1321
• Access Restrictions: インターネット公開
• Data Provider (Database): 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
• Original Data Provider (Database): 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

• Summary, etc.: 層流制御とよばれる、翼上の層流・乱流遷移を遅らせる技術は、超音速で巡航する高速民間輸送機における抗力低減にとって重要である。境界層流の計算、流れの線形安定解析および解析で求めた空間増幅率の積分によって遷移の開始を数値的に予測する。遷移の予測に用いる境界層流は、一般に境界層コードにより計算されてきた。...