| Citation: | ZHANG Kexin, HUANG Hexia, TAN Huijun. Research on aerodynamic design of an ejector nozzle based on TBCC integrated engine[J]. Journal of Aerospace Power, 2025, 40（6）：20230521 doi: 10.13224/j.cnki.jasp.20230521
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The effects of main design parameters of the ejector nozzle, including the length of the main nozzle, the throat area of the ejector nozzle, the position of the throat and the area of the expansion section, on the internal flow-field and thrust performance in the design state were studied through numerical simulations. The results showed that, in order to improve the thrust coefficient of the ejector nozzle, it is advantageous to reduce the length of the main nozzle, appropriately increase the throat area of the ejector nozzle, move the position of the ejector nozzle throat backward and increase the cross-sectional area of the expansion section in the ejector. The influence of various design parameters on the flow mechanism was mainly embodied in the degree of the mainstream expansion and the characteristics of the shear layer. It was verified that the ejector nozzle could achieve good aerodynamic performance within the full operating range (Mach number of 0 to 4). In the design state, the thrust coefficient could reach 0.96.
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