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3-4 喷管及实验段孔壁长度原有的高亚音速风洞圆弧曲线音速喷管性能是良好的,但其长度占实验段结构长度的47.5%,根据国外跨音速风洞资料总结及我们的实验结果,在音速喷管下游需要有一个实验段高度的距离作为低超音速气流加速段,这样余下来可供模型实验用的实验段长度就只占全长的20.6%,显然是不够用的,因此我们重新设计了一个音速喷管,其长度为原长的53.7%,喷管曲线采用Batchelor-Shaw截面积分布律方法,事实证明喷管长
3-4. The Length of the Wall of the Nozzle and the Experiment Section The original high sub-sonic wind tunnel arc curve sound velocity nozzle performance is good, but its length occupies 47.5% of the experimental section length. Based on the data of transonic wind tunnel abroad And our experimental results, there is a need to have an experimental section height downstream of the sonic nozzle as the low-supersonic airflow acceleration section, so that the remaining experimental section length for the model experiment is only 20.6% of the total length, apparently Not enough, so we redesigned a sonic nozzle length of 53.7% of the original length, the nozzle curve using Batchelor-Shaw cross-sectional distribution method, the nozzle length