The numerical simulation technique is used to investigating the isentropic Mach number distribution on the different swept height blade surfaces of a turbine last stage blades.
采用数值模拟技术详细地研究了不同掠高的某蒸汽轮机末级前掠叶片表面等熵马赫数的分布。
The results indicate that passive control technique can reduce peak Mach number on the surface of the airfoil and reduce the adverse pressure gradient, shock is also weakened.
结果表明，被动控制使得沿模型表面的马赫数峰值及过压力梯度明显减小，激波减弱。
The results indicate that passive control technique can reduce peak Mach number on the surface of the airfoil and reduce the adverse pressure gradient, shock is also weakened.
结果表明，被动控制使得沿模型表面的马赫数峰值及过压力梯度明显减小，激波减弱。
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