单面膨胀高超音速尾喷管内流场的数值模拟  

Numerical Simulation of Internal Flow Field in the Single Expansion Ramp Nozzle for the Hypersonic Aero-engine

作　　者：王晓锋[1] 商旭升[1] 陈玉春[1] 蔡元虎[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《弹箭与制导学报》2007年第2期187-189,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对设计的高超音速动力系统用单斜面膨胀喷管流动特点,采用三维质量平均Navier-Stokes方程,空间三阶精度高分辨率NND差分格式及可实现(Realizable)k-ε湍流模型,对所设计的Ⅰ型和Ⅱ型喷管内流场进行了数值模拟,获得了喷管的流场参数分布。计算结果表明:喷管扩散段长度及出口斜切角变化对喷管出口流场会产生影响,Ⅱ型喷管的设计较为合理。The flow fields of single expansion ramp nozzle Ⅰ and Ⅱ for the hypersonic propulsion system are numerically investigated in this paper, by solving the mass-averaged 3-D Navier-Stokes equations, based on the third-order NND ,scheme and realizable κ-ε turbulence model. The numerical results show that the variations of the diffuse segment length and inclined angle of nozzle can affect flow-field at the nozzle outlet; the results also show that the design of nozzle Ⅱ is more reasonable.

关 键 词：喷管 数值模拟 湍流模型 NAVIER-STOKES方程 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]