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.0021a" src="https://static.hindawi.com/articles/mse/volume-2011/293078/figures/293078.fig.0021a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>DLR-F6</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="293078.fig.0021b" src="https://static.hindawi.com/articles/mse/volume-2011/293078/figures/293078.fig.0021b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>OWN (<i>OPT2</i>) geometry</td></tr></table></td></tr></table>

<table>Comparison of surface pressure coefficient contours.</table>

Modelling and Simulation in Engineering

fig21

Figure 21

Figure 21: Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration 