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TAILED AIRCRAFT
CmSe is given by (2.4,8), so (2.6,11) becomes for this case
(* – h’J = V(h – K) – ^ cLSe(h – KJ + ^
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CheJ-^Ls, ‘-‘he,, — — 7—- K* 1 + ~ a. V, |
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, ae bx ( де / St __ K – h – – v v, 1 – d -<*■-T+ ^ |
Using (2.6,4b) this becomes
The difference (h’n — h) is called the control-free static margin, K’n. When representative numerical values are used in (2.6,13) one finds that hn – h’n may be typically about 0.08. This represents a substantial forward movement of the NP, with consequent reduction of static margin, pitch stiffness, and stability.
