摘要
基于线性稳定性的结果,以类似于处理湍流脉动的方式来模化流场脉动,用以研究高超声速的流动转捩,包括转捩起始位置及转捩区长度。研究中采用Faver平均Navier-Stokes方程κ-ε湍流模型,分别以Roe二阶流通量差分分裂格式和Chakravarthy三阶迎风TVD格式进行离散,数值模拟了椭圆锥的高超声速绕流流场,分析比较了不同的湍流转捩机制,并研究了雷诺数的影响规律。结果表明：Bypass转捩机制是传统的高湍流度风洞中模型流动转捩的主控因素。
Based on the liner stability analysis, a approach that treats non-turbulent fluctuations in a turbulence-like manner is used to research supersonic flow transition including onset and extent of transition, Numerical research adopts Faver average Navier-Stokes equations and the k - ε turbulence mode, A second order Roe＇s FDS is introduced to simulated supersonic flow over an elliptic cone, Several transition mechanisms are compared and the Reynold number effect on flow transition is also studied, As a result, bypass mechanism dominates transitional flow over the models put in high intensity, transition onset and transition extent and the distribution of heat flux predicted are agreed with the experiment＇s result, As the Reynold number increases, transition onset is closer to the apex and the extent become shorter.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第1期85-88,共4页
Journal of Astronautics
基金
武器装备预研基金(51413030105HT7105)国家安全重大基础研究(51324)
关键词
流动转捩
高超声速流动
湍流模型
数值模拟
Flow transition
Supersonic flow
Turbulence model
Nttmerical simulation
