前机身/进气道攻角特性的数值与试验研究

Numerical and Experimental Studies on Characteristics Under Angle of Attack for Forebody-Inlet

关键词:  数值模拟  前机身/进气道  大攻角  总压恢复系数  总压畸变指数

Key words:  Numerical simulation  Forebody/Inlet  High angle of attack  Total pressure recovery coefficient  Total pressure distortion index

摘要:

为研究前机身/进气道内外流场的攻角特性，对其一体化模型进行综合求解。将数值计算结果与试验数据进行对比以验证数值方法。分析了不同攻角下前机身对进气道入口气流的影响以及进气道内部流动情况，同时分析了攻角对进气道总压恢复系数和出口总压畸变指数的影响。结果表明:进气道位于机身下侧的布局能在大攻角下降低进气道入口的迎角和马赫数，有效提高飞行极限；在超声来流下，进气道在很宽泛的攻角范围内总压恢复系数都能达到0.94左右，在9°到18°攻角范围内具有较低水平的总压畸变，在此攻角范围之外，总压畸变对攻角的变化很敏感。

Abstract:

In order to study the characteristics of external and internal flow field for forebody-inlet，the united model was simulated. The numerical method has been proved by the comparison between numerical results and the test data. The forebody influence on inlet entrance and internal flow was analyzed at different angles of attack. Furthermore，the angle of attack influence on total pressure recovery coefficient and distortion index was researched. The results show that ventral mounted layout can reduce the angle of attack and Mach number at inlet entrance for high angle of attack，which can improve flight limit. The total pressure recovery coefficient can achieve 0.94 in a broad range of angle of attack under supersonic flow. When angle of attack range is between 9 ° and 18 °，the inlet has a low-level total pressure distortion. However，the total pressure distortion is sensitive to the change of angle of attack when the angle is out of range described above.