Abstract: As the driving system of continuous transonic wind tunnel, compressor's matching design, which considered its operating performance and the general performance of wind tunnel, is one of the key technologies in wind tunnel design. With the development of large continuous transonic and supersonic wind tunnel, the compressor trends to have larger power, higher energy efficiency, wider range, higher precision and so on. The layout scheme of the axial compressor in the 0.6 m continuous transonic wind tunnel, which is a pilot wind tunnel for large transonic wind tunnel, is studied. The location and the scheme of the main compressor are analyzed from the aspects of aerodynamic performance, structural design and control. Also, the integrated design of the wind tunnel and compressor is important for the sake of efficiency. By performance test of compressor in the 0.6 m continuous transonic wind tunnel, while the compressor arranged between the first and the second corner, the feasibility of the layout scheme of external motors and two-end drive, the synchronous control of multi motors and the rectification technology of the compressor's internal flow path is validated. All the compressor's operating performance indicators can fulfill the design-technology requirements well. The studies provide technical support for the construction of large scale continuous transonic wind tunnel.