摘要
以平面叶栅中的二元叶栅模型为试验对象，测量了在不同来流条件下叶片表面流场分布情况及栅后气流参数，分析了不同来流条件下叶片表面附面层流动状态的变化。并借助数值模拟手段重点研究了在不同来流马赫数和冲角下，叶片表面压力梯度对层流附面层向紊流附面层转捩过程的影响，通过利用实验数据分析研究来流条件对转捩过程的影响，为从机理上更深刻地认识叶片表面粘性附面层转捩机制提供了科学参考依据。
A compressor cascade was tested in a low speed two dimensional cascade wind tunnel.The measurements of flow field on blade surface were made at the cascade inlet and exit.Boundary layer development was analyzed under different inlet flow conditions.The pressure gradient on blade surface and their effects on transition from laminar flow to turbulent flow was studied numerically at different inlet Mach numbers and incidences.By means of the experimental data,the viscous boundary layer transition on blade surface was studied in detail.It is very helpful for better understanding of the complex boundary layer transition mechanics.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第3期64-68,共5页
Journal of Propulsion Technology
基金
国家自然科学基金
关键词
压气机叶栅
边界层流
流动分析
航空
叶片
仿真
Compressor cascade,Boundary layer flow,Flow distribution,Transition flow,Influence factor,Experimentation,Numerical simulation
