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It has been reported in literature that the use of protrusion in the combustion chamber of a hybrid rocket motor enhances the regression rate. This study reports careful experiments conducted to show that the improvement in burn rate with protrusions is only up to a certain fraction of the overall burn time. From the results obtained, it is seen that an X/L of 0.5 is the best location for a graphite protrusion. The protrusions are also shown to increase the combustion eficiency by as much as 45 % when placed at an X/L of 0.5. This, more than the improvement in the regression rate is very useful, especially for small scale motors whose combustion eficiencies are otherwise very low. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved
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Publisher | Data powered by TypesetAmerican Institute of Aeronautics and Astronautics |
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ISSN | 0001-1452 |
Impact Factor | 1.868 |
Open Access | No |
Citation Style | unsrt |
Sherpa RoMEO Archiving Policy | Green |