前缘驻点 meaning in Chinese

leading edge stagnation

The method of prediction the discharge coefficients of film cooling holes on the turbine blade suggested by d . a . rowbury et . al has been improved in this paper to fit the computations in the cases of low pressure ratios and the holes in leading edge region especially . the effects of external cross - flow , hole geometry and reynolds number in the hole were taken into account . an additive loss coefficient method is subsequently applied to the test data in order to assess the effect of the external cross - flow
Rowbury等提出的流量系数工程算法进行了改进，计算结果和实验数据的比较表明改进后的新模型使低吹风比和前缘驻点附近流量系数的计算得到了明显的改进，而在高吹风比下仍能保持与实验数据相符，这种算法有可能成为低压比情况下型面气膜冷却的一种通用设计方法。