Fa2004 16.3337-11 X10 Aileron 1 deg Impulse -2sec on then off 15 30 8>0==>right wing up 10 15 Initial adverse yaw == RY cou 10 15 0.005 0.01 time sec Figure 3: Aileron impulse to flight variables Aileron da=ldeg impulse for 2 sec notation, and it is not consistent with the picture on 6-4(from Nelson/ s Since da >0 then right aileron goes down, and right wing goes up -Reids Influence of the roll mode seen in the response of p to application and release of the aileron input. See effect of adverse yaw in the yaw rate response caused by the differential drag due to aileron deflection Spiral mode harder to see Dutch mode response in other variables clear(1 rad/ sec n 6 sec period)Fall 2004 16.333 7–11 0 5 10 15 20 25 30 −4 −2 0 2 x 10−4 β rad Aileron 1 deg Impulse − 2sec on then off 0 5 10 15 20 25 30 −4 −2 0 2 x 10−3 p rad/sec δ a > 0 ==> right wing up 0 5 10 15 20 25 30 −5 0 5 x 10−4 r rad/sec Initial adverse yaw ==> RY coupling 0 5 10 15 20 25 30 −0.01 −0.005 0 φ rad time sec Figure 3: Aileron impulse to flight variables • Aileron δa =1deg impulse for 2 sec. – Since δa > 0 then right aileron goes down, and right wing goes up → Reid’s notation, and it is not consistent with the picture on 6–4 (from Nelson). – Influence of the roll mode seen in the response of p to application and release of the aileron input. – See effect of adverse yaw in the yaw rate response caused by the differential drag due to aileron deflection. – Spiral mode harder to see. – Dutch mode response in other variables clear (1 rad/sec ∼ 6 sec period)