Utility of Multiprotrusion as the Performance Enhancer in Hybrid Rocket Motor

Effect of Protrusion on Combustion Stability of Hybrid Rocket Motor

“…The detailed information about the experimental setup is available in the Refs. [13][14][15]. For a clear understanding, it is also described in this section.…”

“…Besides, it was reported in Refs. [13][14] that the protrusion at 0.2X/L was not effective in disturbing the flow during the combustion as it comes under the influence of head-end recirculation. Due to this, the protrusion at 0.2X/L has not shown much influence on the suppression of the excitation of acoustic modes.…”

“…More details regarding the utilization of the protrusion method in the hybrid rocket motor can be found in Refs. [13][14][15][16][17].…”

“…The present study dealt with the protrusion method considering it's benefits over the other methods used for improving the performance of the hybrid rocket. These benefits include simple configuration, cost-effectiveness, and suitability for different applications such as for flame holding and augmenting the mixing of product gases inside the combustion chamber [13][14][15][16][17]. The protrusion method can be used with a hybrid rocket motor irrespective of the length of the motor; whereas, this feature is not possible with the swirl injection method [14,16].…”

“…It can be understood from Table 1 that most of the past investigations on the protrusion method in hybrid rockets have dealt with the regression rate and combustion efficiency [12][13][14][15][16][17][18][19][20][21][22][23][24]. Studies concerning the effect of protrusion on the combustion stability behavior of hybrid rocket motors are seldom found in hybrid rocket literature.…”