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Experimental Study of the Swirling Oxidizer Flow in HTPBN2O Hybrid Rocket Motor
Joint Authors
Heydari, Mohammad Mahdi
Ghadiri Massoom, Nooredin
Source
International Journal of Aerospace Engineering
Issue
Vol. 2017, Issue 2017 (31 Dec. 2017), pp.1-10, 10 p.
Publisher
Hindawi Publishing Corporation
Publication Date
2017-08-27
Country of Publication
Egypt
No. of Pages
10
Abstract EN
Effects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied.
A hybrid propulsion laboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the operating parameters, like fuel regression rate, specific impulse, and characteristics velocity and combustion efficiency.
Primitive variables, like pressure, thrust, temperature, and the oxidizer mass flow rate, were logged.
A modular motor with 70 mm outer diameter and variable chamber length is designed for experimental analysis.
The injector module has four tangential injectors and one axial injector.
Liquid nitrous oxide (N2O) as an oxidizer is injected at the head of combustion chamber into the motor.
The feed system uses pressurized air as the pressurant.
Two sets of tests have been performed.
Some tests with axial and tangential oxidizer injection and a test with axial oxidizer injection were done.
The test results show that the fuel grain regression rate has been improved by applying tangential oxidizer injection at the head of the motor.
Besides, it was seen that combustion efficiency of motors with the swirl flow was about 10 percent more than motors with axial flow.
American Psychological Association (APA)
Heydari, Mohammad Mahdi& Ghadiri Massoom, Nooredin. 2017. Experimental Study of the Swirling Oxidizer Flow in HTPBN2O Hybrid Rocket Motor. International Journal of Aerospace Engineering،Vol. 2017, no. 2017, pp.1-10.
https://search.emarefa.net/detail/BIM-1157969
Modern Language Association (MLA)
Heydari, Mohammad Mahdi& Ghadiri Massoom, Nooredin. Experimental Study of the Swirling Oxidizer Flow in HTPBN2O Hybrid Rocket Motor. International Journal of Aerospace Engineering No. 2017 (2017), pp.1-10.
https://search.emarefa.net/detail/BIM-1157969
American Medical Association (AMA)
Heydari, Mohammad Mahdi& Ghadiri Massoom, Nooredin. Experimental Study of the Swirling Oxidizer Flow in HTPBN2O Hybrid Rocket Motor. International Journal of Aerospace Engineering. 2017. Vol. 2017, no. 2017, pp.1-10.
https://search.emarefa.net/detail/BIM-1157969
Data Type
Journal Articles
Language
English
Notes
Includes bibliographical references
Record ID
BIM-1157969