Fuel regression-rate characterization on a lab-scale hybrid rocket burning N2O and paraffin-based propellants-Reference-Cited by-同舟云学术

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Fuel regression-rate characterization on a lab-scale hybrid rocket burning N2O and paraffin-based propellants

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

Scaramuzzino Francesca¹,Carmicino Carmine²,Festa Giandomenico²,Viviani Antonio¹,Russo Annamaria²

Affiliation:

1. Second University of Naples

2. University of Naples "Federico II"

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2013-4039

Reference20 articles.

1. TURBULENT BOUNDARY LAYER COMBUSTION IN THE HYBRID ROCKET

2. Hybrid rocket combustion study

Cited by 2 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. Modeling of gas–surface interface for paraffin-based hybrid rocket fuels in computational fluid dynamics simulations;Progress in Propulsion Physics – Volume 11;2019

2. Paraffin-based hybrid rocket engines applications: A review and a market perspective;Acta Astronautica;2016-09

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