Aerodynamics and Design for Ultra-Low Reynolds Number Flight
Aerodynamics and Design for Ultra-Low Reynolds Number Flight
Aerodynamics and Design for Ultra-Low Reynolds Number Flight
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Torque per unit span (g cm)<br />
0.75<br />
0.50<br />
0.25<br />
0.00<br />
0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0<br />
Chapter 6<br />
FIGURE 6.33 OVERFLOW-D <strong>and</strong> rapid analysis method spanwise torque distributions <strong>for</strong> the<br />
four-blade 2.5cm rotor.<br />
The assumption that the discrepancy at the tip region is an artifact of the OVERFLOW-D<br />
analysis does not explain the local differences, as much as 15%, in the prediction of<br />
thrust between the rapid analysis method <strong>and</strong> OVERFLOW-D. The shape of the<br />
distributions are also consistently different, concave in the case of the OVERLFOW-D<br />
analyses <strong>and</strong> convex <strong>for</strong> the blade-element method. This is indicative of distinctly<br />
different downwash distributions.<br />
50,760 RPM, OVERFLOW-D<br />
50,760 RPM, Reduced-order Method<br />
46,790 RPM, OVERFLOW-D<br />
46,790 RPM, Reduced-order Method<br />
40,620 RPM, OVERFLOW-D<br />
40,620 RPM, Reduced-order Method<br />
r/R<br />
131