一种S弯进气道的设计与实验研究

Design and Experimental Study of an S-shaped Inlet

在导弹总体几何尺寸的严格限制下 ,通过特定中心线形状和沿程面积变化规律的控制 ,完成了一种大偏距短扩压的亚声速进气道的设计 ,设计中充分考虑了导弹的气动阻力特性。本文还进行了风洞实验研究 ,得到了进气道的性能参数、速度特性、攻角特性和侧滑角特性 ,结果表明该进气道具有良好的气动性能 (总压恢复系数大于 0 .98)。进气道的出口总压图谱表明 ,前急后缓的中心线形状与前急后缓的面积变化规律的组合对出口总压的均匀分布不利。本研究为 S弯进气道的设计和应用积累了经验 ,提供了实验依据。

Due to the strict constraints of the geometric configuration of a missile, by utilizing a specific centerline distribution and area distribution, an S-shaped inlet with large offset and short diffuser is presented. Furthermore, sufficient considerations of the drag characteristics are given in the inlet design. In order to verify the feasibilities of the design method, a test is conducted in the NH-1 wind tunnel of Nanjing University of Aeronautics and Astronautics. In the experiment, the performance of the inlet is obtained, including the effects on the free stream of Mach number, the attack angle and the yaw angle. Results indicate that the inlet is of good performance with the total pressure recovery coefficient greater than 0 98. Moreover, as shown in the plot of the total pressure distribution at the exit of the inlet, it is evident that the combination of the centerline distribution with rapid turning at the entrance and the area distribution with rapid turning at the exit deteriorate the distortion. Based on the research, more experiences are supplied in the design and application of S-shaped inlet.