Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration

<table class="table-group" width="800px"><tr class="fig-image" id="a"><td><img alt="293078.fig.0019a" src="https://static.hindawi.com/articles/mse/volume-2011/293078/figures/293078.fig.0019a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>32% semispan location</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="293078.fig.0019b" src="https://static.hindawi.com/articles/mse/volume-2011/293078/figures/293078.fig.0019b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>37% semispan location</td></tr></table></td></tr></table>

<table>Comparison of <svg height="18.6" id="M116" style="vertical-align:-5.73167pt" version="1.1" viewbox="0 0 19.7875 18.6" width="19.7875" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
<g transform="matrix(.017,-0,0,-.017,.062,11.4)"><path d="M682 629q-1 -16 -1.5 -72t-2.5 -86l-31 -4q-5 92 -51 129t-139 37q-100 0 -177 -49t-116 -125t-39 -162q0 -122 66 -201t182 -79q83 0 137 42.5t112 128.5l26 -15q-12 -31 -42.5 -88t-45.5 -75q-139 -27 -199 -27q-148 0 -243 81.5t-95 226.5q0 173 129.5 274.5
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<g transform="matrix(.012,-0,0,-.012,12.05,15.475)"><path d="M570 304q0 -108 -87 -199q-40 -42 -94.5 -74t-105.5 -43q-41 0 -65 11l-29 -141q-9 -45 -1.5 -58t45.5 -16l26 -2l-5 -29l-241 -10l4 26q51 10 67.5 24t26.5 60l113 520q-54 -20 -89 -41l-7 26q38 28 105 53l11 49q20 25 77 58l8 -7l-17 -77q39 14 102 14q82 0 119 -36
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</svg> distribution (black line: <i>OPT1</i>, red line: <i>OPT2</i>).</table>

Modelling and Simulation in Engineering

fig19

Figure 19

Figure 19: Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration 