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
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━╋━╋━━━━┫
┃ ┃\ ┃ ┃v ┃ - ┃~ ┃ ┃ ┃ ┃
┃I ┃N ┃\ ┃ ┃,o ┃ ┃ ┃ ┃ ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━╋━╋━━━━┫
┃ ┃ ┃-\ ┃\ ┃\ ┃ ┃ ┃ ┃ ┃
┃I ┃^cr ┃J ┃ ┃ ┃o^ ┃t\ ┃ ┃ ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━╋━╋━━━━┫
┃ ┃ ┃o t~l ┃} ┃.\ ┃. ┃o ┃ ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━╋━╋━━━━┫
┃[ ┃ ┃x ┃ o ┃oo ┃\ ┃ ┃u ┃ ┃
┃[ ┃ ┃ ┃( ┃ ┃ ┃\ ┃ ┃ ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━┻━╋━━━━┫
┃ ┃ ┃ ┃\ ┃ ┃~ ┃_ \k-o ┃N ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃-a 'o\fo. ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━┳━┻━━━━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ l ┃o& ┃
┣━━━━━╋━━━╋━━━╋━━╋━━╋━━╋━━╋━━━━━━┫
┃l "'." " ┃ ┃ ┃ ┃ ┃0 " 20 '﹢~ (derJ
Fig.839 Variation ofnormalvortex asymmetry during wing rock cycle.31
710 PERFORMANCE, STABIUTY, DYNAMICS, AND CONTROL
Ax
T
xl
L
Ax=xl-xt
Fig 8.40 Static anddynamicvortu:breakdownlocations.31
8.8.4 Effectof Sideslip
The etfect of sideslip on the wing rock of slender delta wings like the 80-deg
delta wing is one of damping in nature. In other words, if sideslip is increased,
the wing rock amplitude decreases, and eventually it degenerates into a random,
small- amplitude oscillation.24
8.9 Roll Attractor of Delta Wings
Roll attractor is another interesting phenomenon exhibited by thin, sharp-edged,
highly swept delta wings. The roll attractor is the skady-state roll angle attained
by a free-to-roll model. The leading-edge sweep of delta wings, which exhibits
the existence of mulOple-roll attractors is high but generally below the value that
leads to wing rock. Ty:pical time histories of free-to-roll delta wings with leading~
edge sweeps of 60 and 65 deg at a -. 30 deg are shown in Fig. 8.41.32 The
65-deg delta wing has three roll attractors at 0 and :L21 deg,33 whereas the 60-deg
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 CONTROL4(72)
