Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/5847627/figures/5847627.fig.007a.svgz" name="5847627.fig.007a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Traditional wing without control surface</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/5847627/figures/5847627.fig.007b.svgz" name="5847627.fig.007b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Morphing piezoelectric wing</td></tr><tr class="fig-image" id="c"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/5847627/figures/5847627.fig.007c.svgz" name="5847627.fig.007c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>Traditional wing with rigid trailing edge</td></tr></table>

<div>Aerodynamic load redistribution after aeroelastic deformation.</div>

International Journal of Aerospace Engineering

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Figure 7

Figure 7: Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method 