对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。

This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.

youdao

对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。

This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.

youdao