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Thus, a span ratio of 0.4 and a chord ratio of 0.25 meets the design requirement if the aircraft is cruising at 25 m/s and aileron has a max deflection of 25. The actual roll time may vary due to imperfections in manufacturing, or the cruising speed being different than what is calculated. But this aileron dimensions align with recommendations from RC Model Aircraft Design book and other sources, hence, they should be safe to implement.
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Stall Analysis [WIP]
For analyzing stall, simulation is performed at maximum aileron deflection and at expected cruising speed. Initially, a steady state simulation was run but the plots of residuals, lift & drag had a lot of noise. A transient simulation is also performed, which led to a less oscillating values. Pictures are shown below:
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There are no large vorticities above the aileron, hence no significant sign of stall.
Roll rate and time calculation script:
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