並列タイトル等Flowfield Induced by a Secondary Jet in a Supersonic Conical Nozzle
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-479
一般注記The flowfield induced by secondary gas injection into a supersonic conical nozzle with a 9.6 deg half-angle was investigated experimentally. Mach number and Reynolds number of the main stream at the injection point, without injection, were 2.1 and 7.0×10(exp 6), respectively. Flow direction, Pitot pressure and cone surface pressure over a cross section, and nozzle wall static pressure were measured with the main point of interest being the downstream part of the injection port. Static pressure and Mach number distributions over a cross section were deduced from the Pitot and cone surface pressures. These distributions suggest that the flow downstream of the injection port is composed of three shock waves and five regions. Axial development of the flowfield and the effect of the stagnation pressure ratio of the secondary jet to the main stream on the flow structure were also investigated. Axial variations in the maximum value of the wall static pressure in cross sections were compared with the calculated pressure ratios behind the bow shock and its reflected wave. In addition, axially unsymmetric separation lines caused by secondary injection into an overexpanded nozzle flow are shown along with wall static pressure data.
資料番号: NALTR0479000
レポート番号: NAL TR-479
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44732&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