曝光台 注意防骗
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(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
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