Abstract
The pressure matching and recovery performances of the second-throat supersonic-supersonic ejector have been performed experimentally and numerically in the current study. Schlieren pictures of flow structure in former part of the mixing chamber with varied stagnation pressure ratio of the primary and secondary flows have been taken, and the maximum compression ratios have been obtained. Additionally, the relevant numerical simulations have been performed. The obtained results show that the pressure matching performance of the second-throat supersonic-supersonic ejector is weaker than that of the constant area one, and the pressure recovery performance of the former is better than that of the latter. For the ejectors tested in this paper, the stagnation pressure ratios of the second-throat supersonic-supersonic ejector at the limiting condition are approximately 10% lower than those of the constant area one when the contraction angle of the mixing chamber is 4°, and the maximum compression ratio is 12%–30% higher. When the contraction angle of the mixing chamber is 6°, the pressure matching performance of the second-throat supersonic-supersonic ejector declines sharply, and the pressure recovery performance remains almost the same. When the contraction angle of the mixing chamber is 8°, the supersonic-supersonic ejection phenomenon does not take place any longer.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
