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.0011a.svgz" name="6611300.fig.0011a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Radial distribution of total pressure ratio</td></tr><tr class="fig-image" id="b"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.0011b.svgz" name="6611300.fig.0011b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Radial distribution of total temperature ratio</td></tr><tr class="fig-image" id="c"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/6611300/figures/6611300.fig.0011c.svgz" name="6611300.fig.0011c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>Radial distribution of adiabatic efficiency</td></tr></table>

<div>Computational and experimental spanwise distributions of total pressure ratio, total temperature ratio and adiabatic efficiency at near-peak efficiency condition.</div>

International Journal of Aerospace Engineering

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Figure 11

Figure 11: Engineering Application of an Identification Method to Shock-Induced Vortex Stability in the Transonic Axial Fan Rotor 