The Adjusting Of A High-Speed 2D Cascade Tunnel And Numerical Computation Of The Test Section Flow Field

This paper describes the installation and adjusting process of The High-Speed 2D Cascade Tunnel of our university. Some problems were resovled during the installation and calibration. Based on the former design of the tunnel, it was added a airflow ejector which can adjust the static pressure of the airflow behind the cascades. The design and use of the ejector increased the experiment time effectively. This paper also does some introductions about the theories of control system and adjusting process, mainly describing the control of pressure、mach number and position of probe.In the paper, using the method of CFD numerical simulation, the flow field of test section was studied by 3D numerical simulation technique under different airflow inlet angles. The computation results at Ma equal to 0.78 showed that when the airflow inlet angle of test section is 90o, the mach number avedev isσm<0.0045 in the core field of test section outlet; when the airflow inlet angle of test section is 45o, the mach number avedev isσm<0.0026; It illuminates that the mach number distributes uniform in the whole test section flow field, and the mach number average deviation had arrived at the government military standards. The maximal thickness of the boundary layer is 25mm on the left and right wall, which would have some disadvantageous effect on the flowfield of the cascade tunnel, so it is necessary to suck out the boundary layer on the wall in the cascade experiments.Through the research on this subject, finished the installation and adjusting of the High-Speed 2D Cascade Tunnel, and provide against basis for the cascade experiments, Meanwhile, pointing out some insufficiency of the tunnel, try to find a more practical and exact design method, improving the development level of this kind wind tunnel.