Page 312 - Aeronautical Engineer Data Book
P. 312
1 s Roll damping wing effects dominate 2 dy )c y y + C D y �(a y 2Ss 2 but fin and tailplane contribute 0 s dC D 1 2 dy c – C � � y y �
L y da y 2Ss 2 0 Ma
– – V 1 Ss 2 a 1 F 1 2 Ss a 1 F
(i) wing contribution (i) wing contribution (i) fin contribution (i) wing contribution (ii) fin contribution (i) wing contribution (ii) fin contribution
Rolling moment due to roll rate Yawing moment due to roll rate Sideforce due to yaw rate Rolling moment due to yaw rate Yawing moment due to yaw rate
L p N p Y r L r N r
