给出了一个计算亚、跨音涡轮叶栅叶型损失的数值计算方法。
A new numerical method for predicting the profile loss of turbine blades in subsonic and supersonic flows is presented.
通过叶片表面总压损失系数，证实了先进叶型在流动中可以降低叶型损失。
It is proved that the profile loss can be decreased with the use of advanced blade through the comparison of loss coefficient of blade surface overall pressure.
在改进后的损失模型中，定义了新的叶片负荷系数，并用它作为一个特性准则导出了叶型损失计算公式。
In this improved loss model, a new profile loading coefficient is defined and using it as a characteristic criterion, formula for estimating the profile toss coefficient is derived.
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