INFLUENCE OF FIN ON Clp

The sideslipping airplane gives rise to a side force on the vertical tail (see Sec. 3.9). When the mean aerodynamic center of the vertical surface is appreciably offset from the rolling axis (see Fig. 3.19) then this force may produce a significant rolling mo­ment. We can calculate this moment from (3.9,3). When the rudder angle is zero, that is, Sr = 0, the moment is found to be

ap(~P (t) ~ VpSFzF

INFLUENCE OF FIN ON Clp Подпись: M2 v)

thus

and

Подпись: Эсг SFzF / VA2INFLUENCE OF FIN ON Clp(3.12,1)

Leave a reply

You may use these HTML tags and attributes: <a href="" title=""> <abbr title=""> <acronym title=""> <b> <blockquote cite=""> <cite> <code> <del datetime=""> <em> <i> <q cite=""> <s> <strike> <strong>