Engineering Application of an Identification Method to Shock-Induced Vortex Stability in the Transonic Axial Fan Rotor

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.009a.svgz" name="6611300.fig.009a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>30% span from hub (left: experiment, right: RANS SST)</td></tr><tr class="fig-image" id="b"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.009b.svgz" name="6611300.fig.009b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>70% span from hub (left: experiment, right: RANS SST)</td></tr><tr class="fig-image" id="c"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.009c.svgz" name="6611300.fig.009c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>90% span from hub (left: experiment, right: RANS SST)</td></tr></table>

<div>Comparisons of predicted and measured relative Mach number at three typical blade heights for near stall condition.</div>

International Journal of Aerospace Engineering

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Figure 9

Figure 9: Engineering Application of an Identification Method to Shock-Induced Vortex Stability in the Transonic Axial Fan Rotor 