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Hybrid Combustion with Surface Pyrolysis
https://jaxa.repo.nii.ac.jp/records/34429
https://jaxa.repo.nii.ac.jp/records/344290b461207-9f07-46b5-84d3-7772bde43dea
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2400760.pdf (2.3 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||
|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||
| タイトル | ||||||||
| タイトル | Hybrid Combustion with Surface Pyrolysis | |||||||
| 言語 | en | |||||||
| 言語 | ||||||||
| 言語 | eng | |||||||
| 資源タイプ | ||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||
| 資源タイプ | departmental bulletin paper | |||||||
| 著者 |
OMORI, Satoaki
× OMORI, Satoaki
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| 出版者 | ||||||||
| 出版者 | 東京大学宇宙航空研究所 | |||||||
| 出版者（英） | ||||||||
| 出版者 | Institute of Space and Aeronautical Science,University of Tokyo | |||||||
| 書誌情報 |
en : ISAS report/Institute of Space and Aeronautical Science,University of Tokyo 巻 35, 号 8, p. 199-234, 発行日 1970-06 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | This paper aims at clarifying theoretically the gasdynamical aspects of the combustion in hybrid rocket motors. The model used in this analysis is the two-dimensional steady laminar boundary layer with fuel injection from the fuel surface and chemical reaction in the gas phase. It is also experimentally shown that the combustion occurs in the boundary layer even in practical hybrid rocket motors. The boundary layer flow with complicated boundary conditions is treated by the Rayleigh analogy. The characteristic time for evaporation or sublimation of the fuel from the fuel surface is assumed to be finite and comparable in magnitude with the time for the fuel to diffuse across the boundary layer or for the heat to be transferred from the flame to the fuel surface; heat transfer and diffusion times are of the same order of magnitude, when the Lewis number is of the order of unity. The fuel surface is necessarily in non-equilibrium, and the surface temperature is neither constant nor prescribed along the fuel surface : it is calculated selfconsistently. The result of the calculation shows that surface combustion occurs near the leading edge due to the cooling effect of the oncoming oxidizer. Also, the profiles of the temperature, mass-fractions and velocity, the location of the flame sheet, the point of flame detachment and the fuel regression rate are shown. The flame temperature grows as the flame departs from the fuel surface downstream from the point of flame detachment, and it approaches the adiabatic flame temperature far downstream. The experimental results of Smoot and Price on the dependence of the regression rate on the partial pressure of the active oxidizer are replotted according to the present theory. The present representation shows less dispersion than the original one. | |||||||
| ISSN | ||||||||
| 収録物識別子タイプ | ISSN | |||||||
| 収録物識別子 | 0372-1418 | |||||||
| 書誌レコードID | ||||||||
| 収録物識別子タイプ | NCID | |||||||
| 収録物識別子 | AA00675986 | |||||||
| 資料番号 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 資料番号: SA2400760000 | |||||||
