高超声速风洞两级引射器气动性能试验研究

以中国航天空气动力技术研究院（CAAA）FD-07风洞为对象，进行了马赫数5~6时两级超声速引射器气动性能试验研究。通过二级引射器单级调试、两级引射器联调、主-次流混合调试，获得了引射器运行时的相关数据。通过试验数据分析，得出如下结论:（1）在FD-07风洞引射器马赫数5~6试验中，一级引射器运行压力0.8MPa、二级引射器运行压力1.0MPa时，引射器运行效率较高，中压气源消耗较少；（2）超声速引射器用于维持风洞运行压比，而风洞驻室低压环境（即试验模拟高度能力）主要由主气流状态决定，与引射器关系不大；（3）一级超声速引射器能对主气流干扰、二级超声速引射气流干扰起到很好的隔离作用。进一步明确了FD-07风洞引射器的运行状态，优化了引射器运行压力方案。

Experimental investigation on aerodynamic performance of hypersonic wind tunnel two-stage ejector

The aerodynamic performance of the two-stage supersonic ejector is investigated by the Ma5~6 experiment on the FD-07 wind tunnel of CAAA. The experimental data is acquired by the test of the second stage ejector, the combined test of the first and the second stage ejectors, and the combined test of the main flow and the secondary flow. The conclusion can be organized as followed:(1) The ejector operating efficiency is higher and medium pressure gas consumption is less when the work pressure ratio of the two-stage ejector is setted to 0.8MPa and 1.0MPa, respecticely. (2) The low pressure environment of the test section is mainly determined by the main air flow. As far as the start-up pressure ratio of the wind tunnel is satisfied, the ope-rating parameters of the ejector have little effect on the pressure of the test section. (3) The first-stage supersonic ejector can be well segregated from the main airflow disturbance and the second-stage supersonic airlow interference, which is instructive for the theoretical study of the multi-stage ejector. The research work is carried out with the actual wind tunnel as the object, and effectively solves the problem that the running state of the FD-07 wind tunnel ejector is not clear. The ejector operating pressure scheme has been optimized so to be energy saving, and it has practical significance for the hypersonic wind tunnel performance improvement. The relevant test data can provide a reference for the study of aerodynamic performance of the supersonic ejector.