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- OZAWA Kohei
- Department of Aeronautics and Astronautics, The University of Tokyo
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- SHIMADA Toru
- Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
抄録
In this paper, we extend the exiting method to conduct combustion stability analysis in axial injection hybrid rocket engines to apply for vortex injection systems by introducing the swirl strength as a new input of the linear model, extending the quasi one dimensional flows to axisymmetric three dimensional flows and estimating axial skin-friction coefficient in swirl flows and skin-friction shear stress with blowing by contrasting one with no blowing. Next, to validate the accuracy of the quasi-steady boundary layer combustion model we compare regression rates derived from this model with ones derived from experiments. Then, linearizing the quasi-steady model, we construct unsteady models. Finally, we couple the unsteady boundary combustion model with the thermal time lags model in solid fuels and conduct stability analysis. It is estimated that swirl systems also have a set of unstable poles of natural oscillations and swirl and can be more unstable than axial ones.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 (ists29), Pa_53-Pa_61, 2014
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282680298029312
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- NII論文ID
- 130004679618
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- ISSN
- 18840485
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可