A physics based mathematical model to predict the regression rate in an ablating hybrid rocket solid fuel-Reference-Cited by-同舟云学术

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A physics based mathematical model to predict the regression rate in an ablating hybrid rocket solid fuel

Published:2001-07-08 Issue: Volume: Page:
ISSN:
Container-title:37th Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Akyuzlu K.¹,Kagoo R.¹,Antoniou A.¹

Affiliation:

1. New Orleans, Univ., LA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2001-3242

Reference8 articles.

1. Theoretical investigation of hybrid rocket combustion by numerical methods

2. Analysis of hybrid rocket combustion

3. Akyuzlu K., Antoniou, A., and Kagoo, R, "Theeffect of Radiation on Turbulent Convective Heat transfer over an Ablating Solid, ASME HTD-Vol. 366-2, ASME Publications, New York,pp.45-50.

4. Ozisik,N., 1973, "Radiative Transfer andInteractions with Conduction and Convection.'"'

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1. Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber;AIAA Propulsion and Energy 2021 Forum;2021-07-28

2. CFD Simulation of a Hybrid Rocket Motor with Liquid Injection;47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2011-07-31

3. 2D transient numerical code for hybrid rocket simulations with detailed chemistry;20th AIAA Computational Fluid Dynamics Conference;2011-06-14

4. Two-phase flow effect on hybrid rocket combustion;Acta Astronautica;2009-10

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