Conjugated Combustion and Heat Transfer Modeling for Full-Scale Regeneratively Cooled Thrust Chambers-Reference-Cited by-同舟云学术

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Conjugated Combustion and Heat Transfer Modeling for Full-Scale Regeneratively Cooled Thrust Chambers

Published:2013-07-12 Issue: Volume: Page:
ISSN:
Container-title:49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference
language:
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Author:

Negishi Hideyo¹,Daimon Yu¹,Kawashima Hideto¹,Yamanishi Nobuhiro¹

Affiliation:

1. Japan Aerospace Exploration Agency (JAXA)

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2013-3997

Reference39 articles.

1. LE-X -Japanese Next Liquid Booster Engine

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1. Effect of Inlet and Outlet Manifolds on Regenerative Cooling in LOX/Methane Thrust Chambers;Journal of Thermal Science;2020-12-03

2. Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts;Notes on Numerical Fluid Mechanics and Multidisciplinary Design;2020-10-27

3. Velocity and Temperature Profiles in Turbulent Channel Flow at Supercritical Pressure;Journal of Propulsion and Power;2020-01

4. Heat flux evaluation in a multi-element CH4/O2 rocket combustor using an inverse heat transfer method;International Journal of Heat and Mass Transfer;2019-10

5. Numerical Study of Tip Clearance Effects in a Centrifugal Pump with Unshrouded Impeller for Liquid Rocket Engines;AIAA Propulsion and Energy 2019 Forum;2019-08-16

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