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
Fig.3.13 Sectional (two-dimensional) lift-cunre slope of wings.l
177
tan@/rE-2 =05y -0.5y99
-_
9
(3.18)
1.6
1.4
1.2
1.0
CI a .8
A .6
(per rad)
.4
.2
o
where y90 and ygg are the y coordinates at xlc = 0.90 and 0.99, respectively. For a
given airfoil, this information may be obtained from the given section geometrical
data or from Abbott and Von Doenhoff4 for most of the NACA family airfoils.
Figure 3.13c gives the variation of trailing-edge angle ~rE with thickness ratio for
178 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
q}TE
deg
:E
D
Z
┏━━━━━━━━━━┳━━┳━━━┳━━━┳━━┳━━┳━━━┳━━━━┳━━━━┳━━┳━━┳━┳━┓
┃ I ┃ ┃ ┃ ┃ ┃ ┃ ┃V ┃ ┃ ┃j ┃ ┃ ┃
┃ tl \ ┃ ┃ ┃ ┃ ┃ ┃/J ) ┃ ┃ ┃ ┃( ┃ ┃ ┃
┣━━━┳━━━━━━┻━━┻━━━┻━━━┻━━╋━━┻━━━┻━━━━╋━━━━╋━━╋━━╋━╋━┫
┃ ┃ ┃ ┃ ┃ j ┃ ┃ ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ / ┃ ┃ ┃
┃ ┣━━━━━━━━━━━━━━━━━━━━╋━━━━━━┳━━━━╋━━━━┻━━┫ ┃ ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃/ ┃ ┃ ┃
┣━━━╋━━━━━━┳━━━━━━┳━━━━━━┻━━┳━━━╋━━━━╋━━━━━━━╋━━╋━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
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