计算模型包括尖前缘、菱形前缘、圆形前缘等三种不同前缘形状的机翼。

Numerical investigation of the effects of different leading-edge profiles on vortical flows over a double-delta wing;

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计算结果表明：三种不同剖面形状的前缘可以诱导产生不同的前缘分离，形成的各前缘剪切层的特点也不同。

The results showed that different leading edge profiles could induce different forms of separation and that the induced shear layers are also different.

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采用放大的半圆柱状表面模拟涡轮叶片前缘的形状，对叶片前缘单排及两排圆柱形孔的气膜冷却效率进行了测量。

Film cooling effectiveness of hole rows on leading edge of turbine blade has been studied experimentally. The model is a blunt body with a half cylinder leading edge with two flat side walls.

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