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.