空気吸込式ロケットの研究(Ⅰ)-亜音速モード円筒型二次燃焼器の圧力分布と燃焼性能-

Material type: 文書・図像類

Author: 鎮西, 信夫ほか

Publisher: 航空宇宙技術研究所

Publication date: 1979-04

Material Format: Digital

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Note (General)：: Subsonic(downstream choking) mode combustion in cylindrical secondary combustors of air breathing rockets was investigated. Two different types of exp...

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Material Type: 文書・図像類
Title: 空気吸込式ロケットの研究(Ⅰ)-亜音速モード円筒型二次燃焼器の圧力分布と燃焼性能-
Author/Editor: 鎮西, 信夫
升谷, 五郎
石井, 進一
工藤, 賢司
村上, 淳郎
小室, 智幸
CHINZEI, NOBUO
MASUYA, Goro
ISHII, Shinichi
KUDO, Kenji
MURAKAMI, Atsuo
KOMURO, Tomoyuki
Author Heading: 鎮西, 信夫
升谷, 五郎
石井, 進一
工藤, 賢司
村上, 淳郎
小室, 智幸
CHINZEI, NOBUO
MASUYA, Goro
ISHII, Shinichi
KUDO, Kenji
MURAKAMI, Atsuo
KOMURO, Tomoyuki
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1979-04
Publication Date (W3CDTF): 1979-04
Alternative Title: A Study of Air Breathing Rockets(I)-Pressure Distributions and Combustion Performances of Subsonic Mode Cylindrical Secondary Combustors-
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-573
No. or year of volume/issue: 573
Volume: 573
Pages: 20-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Subsonic(downstream choking) mode combustion in cylindrical secondary combustors of air breathing rockets was investigated. Two different types of experimental apparaturs(A and B) were used. Apparatus A inhaled atmospheric air using ejector exhaust system, so that the air stagnation pressure was kept at a constant one atmosphere. In apparatus B, compressed air was supplied to the secondary combustor, in order to keep air flow rate constant. Axial wall pressure distribution, air flow rate(in apparatus A) or air stagnation pressure(in apparatus B), and the radial distribution of Pitot pressure and temperature(only in apparatus A) at the exit of the secondary combustor were measured. These experimental results were compared with ideal conditions at the exit and the air inlet of the secondary combustor, which were then calculated on the assumption of the complete mixing and burning primary rocket exhaust and air stream. A one-dimensional analysis with the measured wall pressure distribution made it possible to calculate axial distribution of other properties such as Mach number, stagnation temperature, and so on. From the stagnation temperature distribution in a sufficiently long secondary combustor, we determined “effective flame length”lf and used it as a measure of necessary combustor length. The performances of the secondary combustors were well correlated to the non-dimensional combustor length, L/lf.
資料番号: NALTR0573000
レポート番号: NAL TR-573
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ