Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing

<table class="table-group" width="800px"><tr class="fig-image" id="a"><td><img alt="231434.fig.001a" src="https://static.hindawi.com/articles/ijae/volume-2013/231434/figures/231434.fig.001a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>Start state</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="231434.fig.001b" src="https://static.hindawi.com/articles/ijae/volume-2013/231434/figures/231434.fig.001b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>Unstart state</td></tr></table></td></tr></table>

<table>Sketch of shock waves and expansion waves around Busemann biplane.</table>

International Journal of Aerospace Engineering

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Figure 1

Figure 1: Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing 