Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2020/8867199/figures/8867199.fig.002a.svgz" name="8867199.fig.002a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Pintle engine</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2020/8867199/figures/8867199.fig.002b.svgz" name="8867199.fig.002b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Pintle tip</td></tr></table>

<div>Schematic of LOX/GCH<sub>4</sub> rocket engine with pintle injector.</div>

International Journal of Aerospace Engineering

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Figure 2

Figure 2: Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine 