@inproceedings{oai:jaxa.repo.nii.ac.jp:00006623,
 author = {小寺, 正敏 and Kodera, Masatoshi},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {A scramjet engine model with sidewall and ramp compression (called E2R) indicated better engine performance than a conventional sidewall compression type engine under the Mach 8 flight condition in the firing tests at Ramjet Engine Test Facility (RJTF) of NAL. In this study, 3D CFD analysis including chemical reaction was applied to the internal flows of E2R corresponding to the firing tests in order to clarify the working characteristics of the engine in detail by using Numerical Space Engine (NSE). CFD results showed good agreement with the RJTF experimental ones, especially in terms of the amount of combustion. Comparative studies were made on the two cases with and without the ingested boundary layer into the engine inlet by CFD. At a moderate fuel equivalence ratio, the large-scale subsonic region was formed around the step from the isolator to the constant-area combustor section because of the separation of boundary layer on the ramp wall in the both cases. Under this condition, the flow structure in the constant-area combustor section was clearly divided into the fuel rich zone within the separated boundary layer near the ramp wall and the fuel poor one near the cowl side. Therefore the mixing and combustion zones existed around the free shear layer of the separated boundary layer. This fundamental characteristic was independent of the ingested boundary layer. As a result, the effect of the ingested boundary layer on the mixing and combustion efficiencies was small. CFD results confirmed that the inlet/combustor interaction was weaker without the boundary layer ingestion. It was showed clearly by the mutual analyses between CFD and experiment that the removal of the ingested boundary layer was effective in the enlargement of the fuel equivalence ratio without engine unstart and the maximum thrust increment from no fuel condition, not in the improvement of the combustion performance., 資料番号: AA0047427022, レポート番号: JAXA-SP-03-002},
 pages = {119--124},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {CFDによる側壁・ランプ圧縮併用型スクラムジェットエンジンの作動特性解析},
 volume = {JAXA-SP-03-002},
 year = {2004}
}