Effect of the Simultaneous Variation in Blade Root Chord Length and Blade Taper on Helicopter Flight Control Effort

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2017/6325269/figures/6325269.fig.004a.svgz" name="6325269.fig.004a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Original blade</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2017/6325269/figures/6325269.fig.004b.svgz" name="6325269.fig.004b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Blade with variation</td></tr></table>

<div>Illustration of variation in blade root chord.</div>

International Journal of Aerospace Engineering

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Figure 4

Figure 4: Effect of the Simultaneous Variation in Blade Root Chord Length and Blade Taper on Helicopter Flight Control Effort 