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.004a.svgz" name="6611300.fig.004a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Overview of computational domain using 4HO-type mesh topology</td></tr><tr class="fig-image" id="b"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.004b.svgz" name="6611300.fig.004b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Fully gridded tip clearance</td></tr><tr class="fig-image" id="c"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.004c.svgz" name="6611300.fig.004c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>Enlarged view of grid near hub leading edge</td></tr><tr class="fig-image" id="d"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.004d.svgz" name="6611300.fig.004d" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(d) </b>Enlarged view of grid near hub trailing edge</td></tr></table>

<div>Computational grid of NASA Rotor 37.</div>

International Journal of Aerospace Engineering

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Figure 4

Figure 4: Engineering Application of an Identification Method to Shock-Induced Vortex Stability in the Transonic Axial Fan Rotor 