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

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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