Page 313 - Aeronautical Engineer Data Book

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Roll damping wing effects dominate but fin and tailplane contribute Many contributions, but often negligible Yaw damping, for large aspect ratio rectangular wing, wing contribution is appr

2 dy
2 dy c � y y
)c y y dC D da y l F N v(fin)
+ C D y – 2 dy � – L v(fin) b 2 dy l F b
�(a y C �
L y c y y c y y b � –
s 0 s � 0 �C L y h F b l F
1 2Ss 2 1 2Ss 2 � F a 1 F s 0 V F � s �C D y 0 V F V �
– – 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