The airflowcreation and experimental investigation of the models performance in wind tunnels are important steps in analyzing the aerodynamic behavior of flying equipment. Hypersonic wind tunnels require some special considerations due to the high speeds. Setting up this wind tunnels requires a high pressure ratio provided by pressure and vacuum reservoirs. Having set up, testing is possible at a lower pressure ratio, but, it will continue only in a short time due to the limited volume of reservoirs, in particular the vacuum reservoir. Maflow suction from wind tunnel output maintains the pressure ratio and increases the operating time. Annular ejectors is suitable for this purpose. The ejectors are suitable for this function due to the simplicity of operation, manufacturing and maintenance. In the present study, the design and parametric analysiof the ejector system is studied.One-dimensional design and parametric analysis is carried out to reduce the required mass flow rate for single, two-stage and three-stage ejectors, and then, the effect of different parameters are investigated. Design and analysis is accomplished for Mach number 8 in a test section with an area of 10×10 Square centimeters. Furthermore, the validation of the computational code is done with experimental data. In the next section, the numerical simulation is carried outto study the validity of the one-dimensional design assumptions and cover the remaining parameters using CFD software ANSYS_CFX. The effect of the mixing chamber length, the angle of convergence, and primary flow swirl angle are among these remaining parameters. An appropriate agreement was observed by comparing numerical simulation results with one-dimensional design and similar researches. Finally, according to the results, the three-stage ejector system with the convergent mixing chamber in the first and second stages and the total required flow rate of 14.71 Kg/s selected as optimal mode. Also, by changing the swirl angle of primary flow, the flow swirl effect in the third stage mixing chamber were investigated. Finally, 24%decrease in the mass flow ratio was observed at angle of 20 degrees. Keywords: Hypersonic Wind tunnel, Wind tunnel run time, vacuum reservoir, Annular Ejector, One-dimensional design, Numerical simulation.