日本航空宇宙学会誌
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
スクラムジェット用ガス採取管における反応凍結
(1) 理論解析
三谷 徹泉川 宗男平岩 徹夫富岡 定毅谷 香一郎
著者情報
ジャーナル フリー

1998 年 46 巻 539 号 p. 660-667

詳細
抄録

We conducted a sensitivity analysis of engine performance on measurements of gas sampling, pitot pressure and static pressure. It indicates that the heat loss in engine and the insufficient quenching of reactions in the gas sampling probes results in the mismatch in the mass flux through the engines. An analytical study of the reactive flow in probes showed that the introduction of a small heat of reaction with radical recombination to the energy equation yielded a saddle-type singularity in a phase plane for temperature and radical. The separatrix running from the initial point to the saddle point gave the criterion dividing the thermal runaway and the chemical quenching. A one-dimensional reaction code with a full-kinetics confirmed this analytical results.

著者関連情報
© The Japan Society for Aeronautical and Space Sciences
前の記事 次の記事
feedback
Top