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Figure 2


Fig. 2. Alterations in the prediction of the numerical damping model to changes in morphometrics and kinematic parameters. Damping coefficient plotted as a function of (A) stroke amplitude (black line) and frequency (blue line), (B) active amplitude component {Phi}A (black line) and relative duration of the downstroke (blue line), (C) turning rate within a flight saccade (black line) and wing length (blue line), and (D) centre of pressure (black line) and mean drag coefficient (blue line).