@inproceedings{3ae750400d9e49bdb0d7b9f8cb2c51ee,
title = "Velocity field in secondary combustor of ejector-jet",
abstract = "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.",
author = "Kiyoshi Nojima and Toshinori Kouchi and Goro Masuya and Sadatake Tomioka",
year = "2012",
doi = "10.2514/6.2012-5838",
language = "English",
isbn = "9781600869310",
series = "18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012",
publisher = "American Institute of Aeronautics and Astronautics Inc.",
booktitle = "18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012",
note = "18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 ; Conference date: 24-09-2012 Through 28-09-2012",
}