並列タイトル等Three Dimensional Calculation of Flow inside Supersonic Inlet
タイトル(掲載誌)航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16
一般注記A three dimensional Navier-Stokes calculation of flow inside a supersonic mixed-compression inlet, designed for Mach 2.5, was carried out. A multi-block method was applied to the calculation grids. Complex configurations of bleed holes and throat slot were simulated in order to compare the solution with experimental data. As a result, detail information of the flow, which was usually difficult to obtain in an experiment, was obtained. On this inlet under the supersonic flow through conditions, the flow was found to be two dimensional in 90% of spanwise direction. In the vicinity of the side-walls, however, three-dimensional separation occurred along the cowl shock. The separation induced a vortex, and the vortex was stretched and swallowed into the throat slot. The ramp bleed ahead of the cowl-shock-impinge line was found to play an important role for avoiding the separation region to spread. A static-wall-pressure comparison between the results and the experimental data showed reasonable agreement.
資料番号: NALSP0016040
レポート番号: NAL SP-16
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43536&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