曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
M cos A%
Fig. 3.97 Compressribility correc:tion factor K VA (Ref. 1).
E
Tar7 contribution. The contribution ofthe horizontal tail to lateral stability is
usually small and can be ignored. However,if the horizontal tailis comparable in
size to the wing, then the methods given earlier for estimating the wing contribution
can be used.
The vertical tail contribution to lateral stability is given by
zu cos a - lU si
(C,pl)v=C)..v ___ ' ) (3.373)
b
where l,, and zy are, respectively, the horizontal and vertical distances between the
center of gravity and the vertical tail aerodynamic center as shown in Fig. 3.102
and C}-.y is the vertical tail side force. As shown in Fig. 3.102, the rolling moment
arm of the vertical tail side force depends on the angle of attack because the rolling
moment is with respect to the wind axis system. For subsonic speeds, C)..v is given
by Eq. (3.302). Substitution gives
(C;B)v=-kay(1+~8),7, SS)(-bl.-) (3.374)
As said before, there is no general method available for estimating the side force
on vertical tail at supersonic speeds. Datcom] gives an approximate engineering
STATIC STABILITY AND CONTROL
~
b
303
0 .2 .4 .6 .8 1.0 1.2 1.4 . 1.6
--- --~~-
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┃ ┃ ┃ ┃ ┃ ┃ ┃\- ┃~ ┃
┣━━━━╋━━━╋━╋━╋━╋━╋━━━╋━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━━━━╋━━━╋━╋━╋━╋━╋━━━╋━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃~ ┃~ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃'----- ┃::~: ┃~ ┃\ ┃~ ┃~ ┃\ ┃ ┃
┃ ┃ ┃ ┃ ┃~ ┃ ┃ ┃ ┃
┣━━━━╋━━━╋━╋━╋━╋━╋━━━╋━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃cOs ┃ ┃
┣━━━━╋━━━╋━╋━╋━╋━╋━━━╋━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┗━━━━┻━━━┻━┻━┻━┻━┻━━━┻━━━┛
Fig. 3.98 Fuselage correction factor K j (Ref.l).
304 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
(-,,p-,, )..
(per deg>
Aspect Ratio A
02468
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┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
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动力机械和机身手册2(51)
