Effects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied. A hybrid propulsion\nlaboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the\noperating parameters, like fuel regression rate, specific impulse, and characteristics velocity and combustion efficiency. Primitive\nvariables, like pressure, thrust, temperature, and the oxidizer mass flow rate, were logged. A modular motor with 70mm outer\ndiameter and variable chamber length is designed for experimental analysis. The injector module has four tangential injectors and\none axial injector. Liquid nitrous oxide (N2O) as an oxidizer is injected at the head of combustion chamber into the motor. The\nfeed system uses pressurized air as the pressurant. Two sets of tests have been performed. Some tests with axial and tangential\noxidizer injection and a test with axial oxidizer injection were done. The test results show that the fuel grain regression rate has\nbeen improved by applying tangential oxidizer injection at the head of the motor. Besides, it was seen that combustion efficiency of\nmotors with the swirl flow was about 10 percent more than motors with axial flow.
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