一种受总体限制的弹用S弯进气道的设计和实验验证  

Design and experimental study of an S-shaped inlet restricted by missile

作　　者：谢旅荣[1] 郭荣伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《空气动力学学报》2006年第1期95-101,共7页Acta Aerodynamica Sinica

摘　　要：在飞行器总体对发动机进气道长度、偏距和相贯位置有特定要求及叉形弹翼根部空间的限制情况下,设计了一种大偏距、短扩压的S弯进气道。进气道的设计特点是在唇口后保证有尽可能长的S弯扩压段,扩压段在采用合理的中心线变化规律和面积变化规律的情况下,通过变宽度的方法确定截面形状,以满足总体要求。风洞模型实验结果表明:1.进气道具有良好的气动性能,高的总压恢复系数(σ>0.985),较低的周向稳态总压畸变指数(Δσ0<1.0%)和径向稳态总压畸变指数(Δσp<2.8%);2.在一定马赫数下,进气道性能对正攻角和偏航角不敏感,仍保持高的总压恢复系数和低的畸变;3.进气道出口气流紊流度较低(—Tu<2.5%),因此进气道出口截面的总畸变指数低(w<3.0%)。A study of an S-shaped inlet in which the offset and length are restricted and cross sections are influenced by the wings of missile is presented in this paper. In order to improve the flow field at the engine face, the design keeps the length of S-shaped part of the inlet as long as possible. The inlet cross sections are defined by changing width after choosing the inlet center line and area regularity. Wind tunnel tests show that 1）the S-shaped inlet designed have high total pressure recovery（σ 〉 0.985） and low steady total pressure distortion （△σ0〈 1.0% and （△σ0 〈 2.8% ）;2）the performance of the inlet is less affected by incidence and yaw; 3）because the level of the total pressure fluctuation is usual ,the S-shaped inlet has low total distortion （ w 〈 3.0 % ）. So the design of the short S-shaped inlet is practicable.

关 键 词：导弹 S弯进气道设计 风洞实验 总压恢复系数 畸变指数 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]