This study investigates the effects of single, double, and multi-protrusion on the performance of a hybrid rocket with two different L / D ratio motors, mainly 12.5 and 18. Wax and gaseous oxygen were used as fuel and oxidizer, respectively. It has been observed from studies that the performance of a hybrid rocket is sensitive to the number of protrusions and their locations within the motor. Between the two L / D motors, single protrusion was outperformed in the 12.5 L / D motor, whereas double and multi-protrusion were more effective in the 18 L / D motor. The highest improvement in regression rate was observed from the use of three protrusions (0.2, 0.5, and 0.8 X / L ) in both motors. The use of four protrusions (0.2, 0.4, 0.6, and 0.8 X / L ) was more significant in improving the regression rate with the 18 L / D motor than with the 12.5 L / D motor. Upon insertion of protrusion, combustion efficiency was enhanced in the 12.5 L / D motor and decreased in the 18 L / D motor. The 12.5 L / D motor was more stable in terms of the shift in oxidizer-to-fuel ratio than the 18 L / D motor. Studies on exhaust plume reveal that a large amount of unburned fuel comes out of the motor and remains as white smoke for all the protrusion cases tested with the 18 L / D motor.


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    Titel :

    Experimental Studies of Protrusion-Inserted Hybrid Rocket Motor with Varying L / D Ratio


    Beteiligte:
    Dinesh, Mengu (Autor:in) / Kumar, Rajiv (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2020-10-15


    Format / Umfang :

    14 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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