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
fuselage to the leading edge of the exposed wing root chord as shown in Fig. 3.16.
If the integral in Eq. (3.36) is posia;e, then (Xac/Cre)N will be negative, which
implies that the aerodynamic center of the fiiselage nose is ahead o6f the leading
edge of the exposed wing root chord. On the other hand, if the integral is negative,
it':rill be aft of the the leading edge of the exposed wing root chord.
For supersonic speeds,l .
(-)N =l (l. -1)
(3.37)
As suggested in Datcom,l the parameter (XcplIN) can be evaluated using the data
given in Fig. 3.11 for cone-cylinders and ogive-cylinders. The definition of the
nose is given in Fig. 3.16. To use the data of Fig. 3.11, note that lA of Fig. 3.11
now equals ~ of Fig. 3.16 so that we have fA/ fN = l}/ln.
Accordingr to Datcom,i
(-) W,B, = (-...) W
(3.38)
i.e., the influence of the body on the location of wing aerodynamic center is small
and ignored.
The data for estimating (XaclCre)W at subsonic and supersonic speeds are pre-
sented in Figs. 3.19a-3.19f.
The procedure for estimation of(xuc/cre)BcW) at subsonic and supersonic speeds
is as follows:
1) Subsonic:
For pAe > 4.0, where p = .[C~2- and Ae is the exposed aspect ratio of the
wing,
...)B,W,=:+(b~_f )XtanAc/4 (3.39)
where the parcimeter X is given in Fig, 3.20 as a function of b f.max/b.
For pAe.<. 4.0, do linear interpolation as follows: obtain the value of (xoc]
Cre)B(W) for pAt = 4.0 as above using Fig. 3.20 and the value of (Xac]Cre)B(W) for
pAe - 0 using Fig. 3.21. Using these two values, do linear interpolation to obtain
the value of (Xac/Cre)BCW) at the desired value of fiAe that lies between O and 4.
(~-. ) W
( q~)
STATIC STABILITY AND CONTROL
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