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
- 0.2020
' x-, = (-., ) - (-,,,.),;
Cre
-. 0.2020 - 0.5266 '
- -0.3246
xa
-.. = (-,,.) (-: )
c'
- -0.3:
_ }.3246(688~~;2)
- -0.4263
~
Substitution of all these values gives
(Cnp)A.W _ 0.0608]rad
C7- :
= O.OOllldeg
The combined wing contribution because of dihedral and sweep is then given by
(CnP)wing = (-O.OOOICL +O.OO11C2)/deg
The fuselage contribution is given by
(Cnp)B,W, = [-KNKR, (SS ) (b)] 7deg
where KN and KRI are to be obtained from data given in Figs. 3.73 and 3.74.
Using data given in Example 3,2, we get hj : 2.7838 m and h2 - 3.048 m
so that J~ ff/ = 0.9556. Furthermore, we have h - d f.max = 3.048 m so that
h/b f.max -- 3.048l3.2715 = 0.9317, xm~lf = 15.9334l23.2410 - 0.6856, and
ClSB.S = 23.24102l60.75 -. 8.8913. With these values, we get KN - 0.0016.
To find K Rt, we need.to find the Reynolds number based on the fuselagelength lf ,
wluch is 23.2410 m. At an altitude of 8500 m, the kinematic viscosit)r is 3.05 x lO-s
m2/s, and the speed of sound is 305.0 nVs (see Appendix). This gives us a flight
velocity of 213.5 m/s and a Reynolds number (Vlf /v) of 16.27 x l07. Then we
obtain K RI = 2.06 from Fig. 3.74. We have SB.S = 60.75 I112, S = 106.0114 1112,
and b - 17.3228 m. Substituting these values in the above equation, we get
(Cnp)B(W) = -0.0025]deg
. 1
: 7.}
'. .
. '/ '
.:l .:
' .::.: ;
. ~:
"- '
.'.: .
. "-
-'~
290 PERFORMANCE, STABILI-fY, DYNAMICS, AND CONTROL
Now we will evaluate the vertical tail contribution, which is given by
(Cnp.V)nx = kap (1 + ~p ) 7 , V2
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(72)
