摘要
本文研究了 3种超音压气机叶型中弧线几何设计方法 ,讨论了控制叶型前缘进口区曲率的参数及其变化关系 ;进行了叶栅设计和流场数值计算分析 ,结果表明 :设计叶型表面马赫数分布理想 ,激波结构合理 ,但以指数中弧线法最佳。
Three geometric methods for designing supersonic airfoil meanline are studied.The parameters which control curvature in the leading region of airfoil and their variations are considered.The flow fields of the cascade designed with these methods are analyzed.It is shown that the Mach number distribution of designed blade surface is ideal,shock wave structure is reasonable.But the exponential method is superior.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2000年第3期237-240,共4页
Journal of Aerospace Power
关键词
轴流压气机
叶片
叶型
几何设计
axial flow compressor
blade
blade profile
design
