並列タイトル等Non-Steady Flow Field of Two-Dimensional Supersonic Nozzles
タイトル(掲載誌)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-855
一般注記The non-steady flow field of an impulsively started two dimensional nozzle was investigated, using double exposure interferometry. Two straight nozzles, one with a sharp-edged throat and the other with a rounded throat, were inserted into a 60mm × 150mm cross sectional shock tube. Incident shock Mach numbers were 2.0 and 2.4 in air. Continuous monitoring of wave interations, incident shock, secondary shock, Mach stem, and, slip line, were also carried out using a streak camera technique. Time-wise development of the density distribution of the whole flow field showed a datailed structure of the starting process and the wave interactions. The steady flow field upstream of secondary shock obtained by the experiment was compared with a numerical calculation using a finite difference method with a shock capturing procedure. Very good agreement between them was obtained. Double exposure holographic interferometry provides a useful tool for generating a gas dynamic data base for evaluation of numerical calculations.
資料番号: NALTR0855000
レポート番号: NAL TR-855
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45113&item_no=1&attribute_id=31&file_no=1
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)
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