International Journal of Aerospace Engineering / 2017 / Article / Tab 3

Research Article

Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor

Table 3

Motor configurations for tests.

Axial
injector number
Tangential
injector number
Precombustion chamberPostcombustion chamber

0-bench10YesNo
1-S4A114YesNo
2-S4A114YesNo
3-S4A114NoYes
4-S4A114YesNo

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