New Contour Design Method for Rocket Nozzle of Large Area Ratio

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/4926413/figures/4926413.fig.009a.svgz" name="4926413.fig.009a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Pressure</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/4926413/figures/4926413.fig.009b.svgz" name="4926413.fig.009b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Axial velocity</td></tr></table>

<div>Comparison of Mach numbers in different nozzles.</div>

International Journal of Aerospace Engineering

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Figure 9

Figure 9: New Contour Design Method for Rocket Nozzle of Large Area Ratio 