超音速粘性・非粘性干渉を含む圧縮性剥離境界層の解法

Material type: 文書・図像類

Author: 河合, 伸担ほか

Publisher: 航空宇宙技術研究所

Publication date: 1977-08

Material Format: Digital

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Note (General)：: This report first presents finite difference solutions for compressible laminar boundary-layer equations for flows with separation and reattachment. I...

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Material Type: 文書・図像類
Title: 超音速粘性・非粘性干渉を含む圧縮性剥離境界層の解法
Author/Editor: 河合, 伸担
KAWAI, Nobuhiro
Author Heading: 河合, 伸担
KAWAI, Nobuhiro
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1977-08
Publication Date (W3CDTF): 1977-08
Alternative Title: Solutions for Compressible Separated Boundary Layers Including Supersonic Interaction
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-503
No. or year of volume/issue: 503
Volume: 503
Pages: 18-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): This report first presents finite difference solutions for compressible laminar boundary-layer equations for flows with separation and reattachment. In order to avoid separation singularity, an inverse technique is used in which the displacement thickness is prescribed and the pressure is derived from the resulting solution. To eliminate unknown pressure from the whole formulation, a vorticity transfer equation and a modified stream function are introduced. To save computation time and storage, a forward marching procedure is adopted, for which streamwise convection terms must be neglected if the flow is reversed. Solutions are obtained by applying the Crank-Nicolson scheme and imposing certain conditions for convergence. A numerical method is next presented for calculation of interaction between outer supersonic flow and laminar boundary-layer flow including separation and reattachement. An interaction equation is obtained by equating the pressure gradient deduced from the supersonic linear theory and that from the momentum equation evaluated at the wall. The interaction equation is modified by adding an artificial-time term to it, and is solved by applying the alternating direction implicit scheme and using the foregoing inverse technique. Results are shown for boundary-layer flow with reverse flow regions over smooth compression ramps.
資料番号: NALTR0503000
レポート番号: NAL TR-503
Access Restrictions: 限定公開
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