曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

(3.174)
                                             V     (n - l)g .
                                R = -W                           (3.175)
Let SZ :  V]R be the angular velocity about the center of the semicircular path O.
Then, we have
Q - (n - l)g
   V           (3.176)
As a result of this angular velocity, the horizontal Lail experiences an increase in
angle of attack Aat.r as shown in Fig. 3.63. From the geometry, we have
                                It
                             Aar.r = R                             (3.177)
                        It V
                                               = v R                                   (3.178)
            f21t
               = V-            (3.179)
                                               (n - l)l,g
                                = ~2                    (3.180)
e_ _ _/...__
250            PERFORMANCE, STABILtTY, DYNAMfCS, AND CONTROL
\
\
   -
 V
n
    /
-<Flight Path
Fig. 3.63    Induced angle of attack at horizontal tail during a pull-out maneuver.
With An :n - 1,
Actt.r  lr9
 A~ = \/2
Because both Aau and An are assumed to be small, we can write
(3.181)
dry/.r            lr 9
 d z7 - V2                                 (3.182)
       At D, L'  = n W  and at A, L  -  W.. The airplane at Dis disturbedin angle of attack
and load factor compared to the steady lcveJ flight at A. These two disturbances
together lead to a net increase in lift AL so that
or
n-l= AC~
    CL
An   1
dn   1
dCL = CL
(3.183)
(3.184)
(3.185)
(3.186)
(3.187)
Then we have
STATIC STABtLITY AND CONTROL
dcy,.,  dor/.r dn
dCL = dzdCL
  lt9
- 2CL
      lr pgS
N-
 2W
       1
251
(3.188)
(3.189)
(3.190)
= 2p,i                         (3.191)
where /ri - W]pgSI,. The parameter p.i is often called the longitudinal relative
density parameter.
     The total angle of attack of the horizontal tail is given by
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(30)