曝光台 注意防骗
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~
&~ )-= :g ),x- C.. C,. (1-: )
= 0.05+( OO~27) (~~) (1 _ 0.5)
- 0.1175
160 *1000
Vrrim: 3 00
= 44.44 m/s
~
Ku = -(-5.0616) (~0;2~)1450.0.1175
-. 191.6378
~
K' = (1/2)*1.225(-5.0616) .
- -3.1002
N
K2 = 0 - 0.003(0 - 0 + 0) - 0.006(-2,0)
- 0.0120
~
l91.6378
8uim=-( O~003) 31~02 4 44 +0.012)
- -6.4460deg
The stick force gradient is given by
dFs = 2K'V(Kz + Ch8.,8r)
dV
= 2(-3.1002) * 44.44(0.0120 - 0.003[-6.4460l)
- -8.6351Ns/m
The stick force gradient is negative because the aircraft is unstable stick-free.
STATIC STABILITY AND CONTROL
Example 3.5
247
Estimate the elevator effectiveness for a horizontal tail fitted with an elevator and
having the following characteristics: aspect ratio - 3.78, Ac/2 = 45.5 deg, Ce]C =
0.224,A - 0.586, r7t - 0.141, and rlo - 0.61. The airfoil section is a NACA
65A006. Assume that the Reynolds number Ri - 6.1 x l06.
Solution. We have to determine the elevator effectiveness parameter r.
For NACA 65A006 airfoil section, we obtain tan(~rEl2)=0.0616 using
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动力机械和机身手册2(7)
