Journal of Astronautics ›› 2020, Vol. 41 ›› Issue (11): 1369-1377.doi: 10.3873/j.issn.1000-1328.2020.11.001

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Design and Performance Study on Low Density and High Subsonic Ejector Wind Tunnel

ZHANG Zhen, ZHANG Xue wei   

  1. China Academy of Aerospace Aerodynamics, Beijing 100074, China
  • Received:2019-11-13 Revised:2020-03-10 Online:2020-11-15 Published:2020-11-23


A low density and high subsonic ejector wind tunnel is designed based on the Mars atmosphere conditions and Mars airplane speed. The performance of the multi ejector wind tunnel is studied using the numerical method with the ANSYS FLUENTT 15.0. Firstly, the mesh independence is verified. Then, based on the accuracy and cost of time and computational resources, the best mesh is selected to study the wind tunnel performance, and it is found that the Mach number of the test section can reach 0.77 using the ejectors as the power system and the test section static pressure almost keeps constant by choosing 1° inclination angle of the test section up and down wall; increasing the ejector expansion ratio is the effective way to enhance the test section Reynolds number, while decreasing the ejector coefficient and increasing the static pressure gradient of the test section. Therefore, the design of a low density wind tunnel is a combination of many factors, including inclination angle, expansion ratio and so on.

Key words: Low density, High subsonic, Multi ejector; Ejector coefficient, Numerical calculation

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