Aeroelastic Analysis of Wings in the Transonic Regime: Planform’s Influence on the Dynamic Instability

<table class="table-group" id="tab4"><tr><td><table class="table"><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr class="thead"><td class="align_left"> </td><td class="align_center">Swept wing</td><td class="align_center">Curved wing</td></tr><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr><td class="align_left">First bending mode: Case <svg height="8.55521pt" id="M47" style="vertical-align:-0.2063904pt" version="1.1" viewbox="-0.0498162 -8.34882 6.36303 8.55521" width="6.36303pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M241 635C89 635 35 457 35 312C35 153 89 -12 240 -12C390 -12 443 166 443 312C443 466 390 635 241 635ZM238 602C329 602 354 454 354 312C354 172 330 22 240 22C152 22 124 173 124 313S148 602 238 602Z" id="g113-49"></path><glyph.data ascent="3473" descent="-2876" horiz-adv-x="480" vert-adv-y="480"></glyph.data></g></svg></td><td class="align_center">1.058 Hz<br/>Mode N. 1</td><td class="align_center">0.916 Hz<br/>Mode N. 1</td></tr><tr><td class="align_left">First torsion mode: Case <svg height="8.55521pt" id="M48" style="vertical-align:-0.2063904pt" version="1.1" viewbox="-0.0498162 -8.34882 6.36303 8.55521" width="6.36303pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M241 635C89 635 35 457 35 312C35 153 89 -12 240 -12C390 -12 443 166 443 312C443 466 390 635 241 635ZM238 602C329 602 354 454 354 312C354 172 330 22 240 22C152 22 124 173 124 313S148 602 238 602Z" id="g113-49"></path><glyph.data ascent="3473" descent="-2876" horiz-adv-x="480" vert-adv-y="480"></glyph.data></g></svg></td><td class="align_center">12.633 Hz<br/>Mode N. 8</td><td class="align_center">12.733 Hz<br/>Mode N. 9</td></tr><tr class="table-tr"><td colspan="3"><hr class="tbody-hr"/></td></tr></table></td></tr></table>

Results of modal analysis: Case <svg height="8.55521pt" id="M46" style="vertical-align:-0.2063904pt" version="1.1" viewbox="-0.0498162 -8.34882 6.36303 8.55521" width="6.36303pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M241 635C89 635 35 457 35 312C35 153 89 -12 240 -12C390 -12 443 166 443 312C443 466 390 635 241 635ZM238 602C329 602 354 454 354 312C354 172 330 22 240 22C152 22 124 173 124 313S148 602 238 602Z" id="g113-49"></path><glyph.data ascent="3473" descent="-2876" horiz-adv-x="480" vert-adv-y="480"></glyph.data></g></svg> (no fictitious moments of inertia were added to finite element models).

International Journal of Aerospace Engineering

tab4

Table 4

Table 4: Aeroelastic Analysis of Wings in the Transonic Regime: Planform’s Influence on the Dynamic Instability 