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┃        ┃          ┃            ┃                ┃      ┃
┃        ┃          ┣━━━━━━┫                ┃      ┃
┃        ┃          ┃            ┃                ┃      ┃
┣━┳━━┻━━━━━┻━━━━┳━╋━━━━━━━━╋━━━┫
┃  ┃                          ┃  ┃                ┃      ┃
┃  ┃                          ┣━╋━━━━━━━━╋━━━┫
┃~ ┃      )--         \-      ┃\ ┃~l/             ┃p)vo  ┃
┃;TA8LE                        ┃  ┃                ┃      ┃
┃  ┃(REFElIENCEE17)           ┃/ ┃                ┃      ┃
┃  ┃        I              I  ┃  ┃                ┃      ┃
┃  ┣━━━━━━━━━━━━━┫  ┃                ┃      ┃
┃  ┃WATER TUNPIEL             ┃  ┃                ┃      ┃
┃  ┃          A (X/Co}        ┃  ┃                ┃      ┃
┃  ┃                          ┣━╋━━━━━━━━╋━━━┫
┃  ┃        ( pi 5o}          ┃  ┃                ┃      ┃
┣━┻━━┳━━━━━┳━━━━┻━┫                ┃      ┃
┃        ┃          ┃            ┃                ┃      ┃
┗━━━━┻━━━━━┻━━━━━━┻━━━━━━━━┻━━━┛
 tI
-0.2
o       I       ie       z4      3z      40
AN(;LE OF AITACX -a.OEG
-0 -4
-oJ
Fig. 8.13    Effect of asymmetric vortex breakdown on lateral stability at high angles
of attack.iz (Courtesy AGARD.)
around the *vertical tail. The lift on the windward side decreases and that on the lee
side slightly increases. As a result, the delta wing experiences a destabilizing effect
in roll as indicated by the increase in the lateral stability parameter Cip (Fig. 8.13).
      This destabilizing.effect in rollincreases with angle of attack, and the maximum
reduction in lateral stability level occurs approximately at the same angle of at-
　
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