論文

2012年

Velocity field in secondary combustor of ejector-jet

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
  • Kiyoshi Nojima
  • ,
  • Toshinori Kouchi
  • ,
  • Goro Masuya
  • ,
  • Sadatake Tomioka

2012-5838
記述言語
英語
掲載種別
研究論文(国際会議プロシーディングス)
DOI
10.2514/6.2012-5838
出版者・発行元
American Institute of Aeronautics and Astronautics

Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

リンク情報
DOI
https://doi.org/10.2514/6.2012-5838
Scopus
https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85086493139&origin=inward
Scopus Citedby
https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=85086493139&origin=inward
URL
http://arc.aiaa.org/doi/pdf/10.2514/6.2012-5838
ID情報
  • DOI : 10.2514/6.2012-5838
  • SCOPUS ID : 85086493139

エクスポート
BibTeX RIS