Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector
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概要
- 論文の詳細を見る
A comprehensive design method for a LOX/Liquid-Methane (L-CH4) rocket engine combustor with a coaxial injector and the preliminary design of the regenerative cooling combustor with 100-kN thrust in vacuum at a combustion pressure of a 3.43 MPa are presented. Reasonable dimensions for the combustor that satisfy the targeted C* efficiency of more than 98% and combustion stability are obtained.
- 2009-11-04
著者
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Yatsuyanagi Nobuyuki
Formerly Kakuda Res. Center National Aerospace Lab.
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Yatsuyanagi Nobuyuki
Kakuda Research Center National Aerospace Laboratory
関連論文
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