複合サイクルエンジンのエジェクタ・モード実験のシミュレーション

Material type: 文書・図像類

Author: 長谷川, 進ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-11-01

Material Format: Digital

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Note (General)：: Rocket Based Combined-Cycle (RBCC) engines are currently being explored as advanced propulsion for space transportation. JAXA has been conducting RBCC...

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Material Type: 文書・図像類
Title: 複合サイクルエンジンのエジェクタ・モード実験のシミュレーション
Author/Editor: 長谷川, 進
谷, 香一郎
Hasegawa, Susumu
Tani, Koichiro
Author Heading: 長谷川, 進
谷, 香一郎
Hasegawa, Susumu
Tani, Koichiro
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-11-01
Publication Date (W3CDTF): 2006-11-01
Alternative Title: Numerical simulation of the ejector-jet-mode experiment of RBCC engine
Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度　宇宙航空研究開発機構　総合技術研究本部　宇宙科学研究本部　研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
No. or year of volume/issue: JAXA-SP-06-006
Volume: JAXA-SP-06-006
Pages: 123-128
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: ロケット組込複合サイクルエンジン
宇宙機推進
流れの分布
計算流体力学
マッハ数
非構造格子
数値シミュレーション
衝撃波
渦度
圧力分布
rocket-based combined-cycle engine
spacecraft propulsion
flow distribution
computational fluid dynamics
Mach number
unstructured grid
numerical simulation
shock wave
vorticity
pressure distribution
Target Audience: 一般
Note (General): Rocket Based Combined-Cycle (RBCC) engines are currently being explored as advanced propulsion for space transportation. JAXA has been conducting RBCC engine research by using various experimental facilities. In order to clarify the experimental results and contribute to the improvement of designing, the analysis of the RBCC engine in an ejector-jet mode was carried out using the CFD (Computerized Fluid Dynamics) code developed in-house for unstructured grids. CFD replicated the basic flow structures in regard with barrel shocks and pseudo-shock waves. Two cases of Mach numbers (i.e., M = 1, 1.1) entering to the combustor were simulated and remarkable differences were found on the subsonic areas in the flowfields. The effect of Mach number was found to be one of the important parameters for better match to the experimental data. Vorticity and mixing were also investigated. In addition to the transverse vorticity, the streamwise vorticity were generated in the air flow, and they stirred and affected the nitrogen/air mixing.
資料番号: AA0049500027
レポート番号: JAXA-SP-06-006
Access Restrictions: 限定公開
Periodical Title (NCID): AA11984031
https://ci.nii.ac.jp/ncid/AA11984031
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