Abstract: In the wind tunnel tests, the method of decreasing stagnation pressure is usually adopted to expand the simulation scope of Reynolds number. Compared with the normal pressure test, in the low Reynolds number situation, the accuracy of the test data is directly affected by whether or not the change of the flow field is obviously and whether or not the quality of the flow field satisfies the index. In order to study the influence of Reynolds number on the 0.6m continuous wind tunnel performance, the relevant tests were carried out in the 0.6m continuous wind tunnel. Based on arrangement and analysis of the tests data, the results were given. It shows that: (1) The Reynolds number has obvious effect on the performance of the compressor, stagnation pressure control precision, Mach number control precision, the flow uniformity etc. When Re_c<5×10⁵(c=0.1√A is the cross-sectional area of the test section),the effect of Reynolds number on the performance of wind tunnel is obvious. The smaller the Reynolds number is, the greater the effect is. (2) The 0.6m continuous wind tunnel can accuratly manifest the influence law of the effects of Reynolds number on the flow field performance of the wind tunnel and the force test data. Therefore, it is a good test platform for the capability research on aircraft, airfoil, engine, etc., at low Reynolds number.