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

Just as wing affects the fuselage flow field, fuselage induces a crossflow that affects
the spanwise lift distribution over the wing. The fuselage interference effects on
the wing are generally small for configurations with large wing-span-to-body-
diameter ratios typified by conventional long-range subsonic airplanes. For such
configurations, lift-curve slope of the wing in the presence of the fuselage can be
assumed to be equal to that of an isolated wing.
  xo.P. -4
  11
      t
(fnctionof -3
body length)
Z
STATIC STABILITY AND CONTROL
175
iAA
,fN
fN=
bfZ fA
i
b f ,mtu
T]
   lA
- bTma.
 Xc.p.
 17r .4
(fiactum of
bodylength) .3
E
.4} .6  .8  i.6 .
 fN
a) Ogive-cylinder
.6_fN .4  -2  0
   q
                                                                                                                         
┏━┳━┳━━━┳━━━┳━━┳━━━━┳━━━┳━━━┳━━┳━━━┳━━━┳━━┳━━━┳━┳━┳━┳━┳━┳━┳━┓
┃  ┃  ┃I:A   ┃      ┃    ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━━━┻━━━┻━━╋━━━━╋━━━╋━━━╋━━╋━━━╋━━━╋━━╋━━━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃   - r\             ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━━━┳━━━┳━━╋━━━━╋━━━╋━━━╋━━╋━━━╋━━━╋━━╋━━━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃' fN  ┃      ┃.5  ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┃  ┃  ┃-/    ┃:/t   ┃N-  ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━━━╋━━━╋━━╋━━━━╋━━━╋━━━╋━━╋━━━╋━━━╋━━╋━━━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃  ┃      ┃      ┃    ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┣━╋━╋━━━╋━━━╋━━╋━━━━╋━━━╋━━━╋━━╋━━━╋━━━╋━━╋━━━╋━╋━╋━╋━╋━╋━╋━┫
┃  ┃- ┃      ┃      ┃    ┃        ┃      ┃      ┃    ┃      ┃      ┃    ┃      ┃  ┃  ┃  ┃  ┃  ┃  ┃  ┃
┃  ┃  ┃      ┃      ┃    ┃ 1      ┃      ┃   N  ┃    ┃      ┃      ┃    ┃      ┃- ┃  ┃  ┃  ┃  ┃  ┃  ┃
　
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 CONTROL1(106)