初步探讨了二维翼型前、后缘襟翼的偏转位置对气动效率的影响。
The influence of airfoil's leading and trailing flaps' deflection location on aerodynamic efficiency is also discussed primarily.
传统的后缘襟翼有助于延缓失速到一个更高的升力系数，但只有有限的成效。
Conventional trailing-edge wing flaps help delay the stall to a higher lift coefficient, but only with limited effectiveness.
研究表明：微型后缘装置明显改变了襟翼后缘弯度，对襟翼流动产生有利诱导作用，拓展加长了增升装置的有效“气动弦长”，是一种附加“气动襟翼”。
The study shows that: Mini-TED changes the curvature of trailing edge and increases effective aerodynamic chord length for high lift system, is an additional 'aerodynamic flap'.
以典型三段翼型为对象，采用数值模拟方法，研究了在襟翼上增加微型后缘装置提高增升装置效率的可行性；
Choosing typical three element airfoil and based on numerical simulation method, the feasibility of MINI-TED to improve aerodynamic performance of high lift system is studied.
以典型三段翼型为对象，采用数值模拟方法，研究了在襟翼上增加微型后缘装置提高增升装置效率的可行性；
Choosing typical three element airfoil and based on numerical simulation method, the feasibility of MINI-TED to improve aerodynamic performance of high lift system is studied.
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