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THE DERIVATIVE C„
The side force due to rolling is often negligible. When it is not, the contributions that need to be considered are those from the wingf and from the vertical tail. The vertical-tail effect may be estimated in the light of its angle-of-attack change (Fig. 8.12) as follows. Let the mean change in a. F (Fig. 8.2) due to the rolling velocity be
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V dp
where zp is an appropriate mean height of the fin. Introducing the
■f For the effect of the wing at low speeds, see ref. (8.4).
Aop=-^2|?-|^ (8.6,1)
The incremental side-force coefficient on the fin is obtained from Aa^.,
A 0Vr = aF &<xF = – aFp[ 2 (§-6,2)
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where aF is the lift-curve slope of the vertical tail. The incremental side force on the airplane is then given by
