Study on the side-inlet dump combustor of solid ducted rocket with reacting flow

Author:

CHEN L.1,TAO C.1

Affiliation:

1. Chung-Shan Institute of Science and Technology,Lung-Tan, Republic of China

Publisher

American Institute of Aeronautics and Astronautics

Reference14 articles.

Cited by 8 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献

1. Numerical Simulation of Reacting Flow Field in a Solid-Propellant Ducted Rocket;Energy and Exergy for Sustainable and Clean Environment, Volume 2;2022-09-19

2. Study on numerical simulation of flowfield in afterburner for ducted rocket;Selected Papers from Conferences of the Photoelectronic Technology Committee of the Chinese Society of Astronautics 2014, Part I;2015-03-04

3. Inlet Geometry and Equivalence Ratio Effects on Combustion in a Ducted Rocket;Journal of Propulsion and Power;2015-03

4. Inlet Geometry Effects on the Internal Performance of a Variable Flow Ducted Rocket Combustor;49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference;2013-07-12

5. Predictions of swirling flow in sudden‐expansion dump combustor with flameholder side‐inlet using two‐step combustion model;International Journal of Numerical Methods for Heat & Fluid Flow;1999-11-01

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