Comparison of analytical and wind-tunnel results for flutter and gust response of a transport wing with active controls

summary of these results is presented in the following table : ~ ~~~ Gain margin, Phase margin, Description dB deg Negative Positive Negative " Pre-test Entry 2 -6 -8 1.5 -78 12 Entry 1 4.3 -5.6 -62 31 -a. 1 5.8 -75 45 I I I I 0.0064 .0035 .0035 Actuator defined by The predominant effect of reducing c3 is to decrease the gain and phase margins. The modified-actuator transfer function tends to rotate the Nyquist diagram clockwise about the origin. This produces a significantly lower positive phase margin and a lower positive gain margin. These results indicate that for this model, the damping coefficient in the flutter mode and the actuator transfer function play a significant role in establishing the stability margins for the control law. Since the bulk of the experimental data on control law 1 was gathered during the second tunnel entry, the predicted results for this case are presented (i.e.,