基于轴对称喷管的三维内收缩进气道的设计与初步评估

3D inward turning inlet design basing on axisymmetric nozzle and its preliminary assessment

介绍了基于逆置等熵轴对称喷管的三维内收缩进气道的设计方法,并对设计的进气道的气动性能进行了初步评估。轴对称逆置等熵喷管采用特征线方法生成,以3°截短逆置喷管流动为基准流场,定义进气道出口为圆形截面,采用流线追踪方法和三维造型工具,生成了三维内收缩的超声速进气道,内收缩比CR=6.18。采用自主CFD软件分析了设计的内收缩进气道性能。无粘和粘性湍流计算表明,在设计点、起动状态下流线追踪进气道出口总压恢复系数高,流动核心区较为均匀。

The design method for inward turning inlet basing on inverse axisymmetric nozzle is described and preliminary aerodynamic performance of this inlet is conducted. Characteristic method is used to design the inverse isotropic axisymmetric nozzle. 3D inward turning inlet is designed basing on the 3° cutting inverse nozzle when inlet exit plant is defined by circle and streaming tracing method and 3D manufacture tool are used. Independently developed CFD software is used to simulate the aerodynamic performance of the inlet. Inviscid and turbulence simulation show that under start condition total pressure recovery is high and core flow is uniformity at inlet exit plan.