曝光臺(tái) 注意防騙
網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者
┃~-.................i;'.., ┃ ! ┃ ┃
┃ . -: --:-- ┃ ┃ ┃
┣━━━━━━━━━━━━━━━━━━━━┻━━━┻━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┫
┃.1 0.2 0.3 0.4 0*5 0.6 0.7 0.8 0.9 .' ┃
┗━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┛
2bL
b
Fig 432 The parameter (trp)WB at subsonicspeeds/
The calculated values of Cmq at subsoruc and supersonic speeds are shown in
Fig. 4.33b.
CLn: Because the given configuration is tailless, we have CIA, - (CLtr)WB, which
is given by Eq. (4.527). The term (Cr.&)e was evaluated at subsonic speeds using
Eq. (4.528) and Datcom data/ at supersonic speeds. The body contribution was
evaluated using Eq. (4.530). The calculated values of Curt are shown in Fig. 4.34a.
Cmdl: We have Cm& - (Cm~t)Ha?, which is given by Eq. (4.539). The term (Cm t)e
was evaluated at subsonic and supersonic Mach numbers using Eq. (4.540) and
Datcom data] The body contribution was evaluated using Eq. (4.543).
The calculated values of Cm& are shown in Fig. 4.34b.
Lateral directional dynamic derrvatives.
Cyp: Wehave
C7p = (Cyp)W + (Cyp)V
For subsoruc speeds, the wing contribution was evaluated using Eq. (4.548). The
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 423
-0 -2
t!
8 _3
cr
E
O _4
a)
Alpha=4
┏━━━━━━━━━━━━━━━━━━━━━━━┓
┃ l....r. ┃
┃_.....CF$6. "',*...*.*... X"' _A-[e__e__-e--e ┃
┃ :-'-.'- ┃
┃-.. .~ 7~- "',"""."'..""........ ┃
┃- N. \/ ┃
┃ .l.... ┃
┗━━━━━━━━━━━━━━━━━━━━━━━┛
o 0.5
1-5 2 2.5 3 3.5 4
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL3(22)
