一种高亚音速弹用S弯进气道设计及其特性

Design and Performance of S-shaped Inlet for High Subsonic Missiles

针对导弹进气道的结构特点 ,在前人的工作基础上总结出一种适合导弹使用的大偏距、短扩压 S弯进气道的设计方法。该方法通过变更中心线、面积规律、唇口形状和喉道位置等参数完成进气道的设计。应用本文中使用的 S弯进气道的数学描述方法 ,可以方便地完成 S弯进气道的几何造型工作 ,实现此类导弹用 S弯进气道的参数化设计 ,生成的造型数据也可以为 CFD和 CAM使用。此外 ,作为验证 ,文中应用此方法设计了一个椭圆进口的 S弯进气道 ,并进行了模型的风洞实验。实验结果表明 ,使用本文方法设计的弹用 S弯进气道可以达到较好的气动性能 。

Considering the structure characters (large offset and short diffuser) of missile inlet, a design method of the S shaped inlets for a high subsonic missiles is presented. This approach covers the main parts of inlet design, such as alternating the inlet centre line and area regularity, choosing the inlet lip and the parameters of the throat. By CAD technique this design method can efficiently give profiles of an S shaped inlet. Based on the approach output data, an S shaped inlet model including the missile body equipped with the inlet was made. Experiment verifies this method and the inlet performance. Experimental results show that the design of the S shaped inlet is practicable, and the S shaped inlet has high performance.