2m×2m超声速风洞引射器气动设计

采用一维气体引射器流动特性方程计算了该等面积混合引射器在不同运行状态下的性能参数,设计增压比为2.1~2.7,引射系数为0.392~0.651,综合结构设计要求确定引射喷嘴数目为24个,径向布置两层,面积比为0.235.引射器1∶13缩比模型的试验结果与计算值具有良好的一致性,5个设计状态下的实测增压比均略高于设计值.2m×2m超声速风洞调试时因整体参数调整导致引射器在某些工作状态偏离了设计点,但增压比与引射系数的对应关系仍与设计结果基本一致,引射器总体性能指标满足风洞试验需求.

Aerodynamic design of the ejector of 2m×2m supersonic wind tunnel

The performance parameters of the ejector were analyzed and computed based on one-dimensional gas dynamic equations under different conditions. The ejector was characterized by multi-nozzles and constant-area mixing. The design compression ratio was 2.1 to 2.7, and the ejection coefficient was 0.392 to 0.651. Twenty four nozzles were installed on two layers, with the area ratio of 0.235. The computational results have good accordance with the 1:13 scale pilot ejector test results. The five experimental compression ratios were a little higher than the design values. Although the operating parameters of the ejector were partly deviated from the design values according to the overall adjustment, the compression ratios and ejection coefficients were still consistent with the computed values. The debugging results of the 2m×2m supersonic wind tunnel show that the performance of the ejector meets the requirements of testing.