发现单纯改变涡襟翼的形式和参数能提高减阻效果，但不能改变小迎角下升力过小的现象。
It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in low angle of attack condition.
发现单纯改变涡襟翼的形式和参数能提高减阻效果，但不能改变小迎角下升力过小的现象。
It is found that the variation of planforms and geometrical parameters can effect only the drag reduction but little to the low lift in low angle of attack condition.
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