Combustion Characteristics in Rotating Detonation Engines

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/8839967/figures/8839967.fig.007a.svgz" name="8839967.fig.007a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Global view</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/8839967/figures/8839967.fig.007b.svgz" name="8839967.fig.007b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Transient phase, LPD</td></tr><tr class="fig-image" id="c"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/8839967/figures/8839967.fig.007c.svgz" name="8839967.fig.007c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>Steady phase, SRDW</td></tr><tr class="fig-image" id="d"><td><object data="https://static.hindawi.com/articles/ijae/volume-2021/8839967/figures/8839967.fig.007d.svgz" name="8839967.fig.007d" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(d) </b>Transition from LPD to SRDW</td></tr></table>

<div>Pressure traces obtained by S1 and S2 for the air mass flow rate 605 g/s.</div>

International Journal of Aerospace Engineering

Combustion Characteristics in Rotating Detonation Engines

Figure 7