| Wind tunnel is the most basic laboratory equipment in the development of aircraft and the study of aerodynamics. So far, most experiments in aerodynamics were done in wind tunnels. The level of the aviation development in a nation could be reflected through the construction scale and level of the wind tunnel.The main task of this project is to design rectangular low-speed wind tunnel. Firstly, the models of the wind tunnel contraction with four different type of profile equations were numerically stimulated. The optimum profile equation of the wind tunnel contraction was obtained through analyzing relevant parameters. Then, the wind tunnel contractions from the optimum equation of different length were also numerically stimulated. The effect caused by the change of the length was observed, thus the optimum length was determined.The main context of this paper is to design the relevant components of the wind tunnel. The function of the diffuser is to decrease the flow velocity and increase the static pressure. The main factor affecting the diffuser is the diffusion angle. In the steady flow section, the aim is to achieve uniform low or reduce the turbulence intensity. The wind tunnel contraction was processed according to the point coordinate calculated from the optimum profile equation which is the results of former numerical stimulation. In the test section, the flow field should have a good quality and the test components need to be installed easily and adjusted its position conveniently.After installation of the wind tunnel, the data of the flow field of the wind tunnel was measured in order to analyze the floe field quality. For the study of the wind tunnel experiments, the data measured from the experiment is dependable. Therefore, the accuracy of numerical simulation could be tested. By flow filed calibration, the flow field was technically and comprehensively assessed. The quality of the wind tunnel through the analysis of measured pressure, velocity and flow direction can met the design requests. |