Determination of Regression Rate in an Ablating Hybrid Rocket Solid Fuel Using a Physics Based Comprehensive Mathematical Model-Reference-Cited by-同舟云学术

Determination of Regression Rate in an Ablating Hybrid Rocket Solid Fuel Using a Physics Based Comprehensive Mathematical Model

Published:2002-07-07 Issue: Volume: Page:
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Container-title:38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
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Author:

Akyuzlu K.,Antoniou Antonis,Martin Michael

Publisher

American Institute of Aeronautics and Astronautics

Reference8 articles.

1. Analysis of hybrid rocket combustion

2. Knuth, W., and Grammer, D. and Chiaverini, M., and Sauer, J., 1998, " Preliminary CFD Analysis of the Vortex Hybrid Rocket Chamber and Nozzle Flow Field," AIAA Paper, 34thAIAA/ASME/ASEE Joint Propulsion Conference andExchibit,July,13-15, 1998, Cleveland,OH.

3. Chiavarini, M. J. et. al. 2001, "Regresson Rate and Heat TransferCorrelationsforHybridRocketCombustion,"JournalofPropulsionandPower,Vol;17,No.1,pp.99- 110.

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